US7527702B2 - Nickel-base alloys and methods of heat treating nickel-base alloys - Google Patents
Nickel-base alloys and methods of heat treating nickel-base alloys Download PDFInfo
- Publication number
- US7527702B2 US7527702B2 US11/544,984 US54498406A US7527702B2 US 7527702 B2 US7527702 B2 US 7527702B2 US 54498406 A US54498406 A US 54498406A US 7527702 B2 US7527702 B2 US 7527702B2
- Authority
- US
- United States
- Prior art keywords
- nickel
- base alloy
- phase
- alloy
- precipitates
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime, expires
Links
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 336
- 239000000956 alloy Substances 0.000 title claims abstract description 336
- 238000000034 method Methods 0.000 title claims abstract description 50
- 239000002244 precipitate Substances 0.000 claims abstract description 224
- 230000032683 aging Effects 0.000 claims description 114
- 238000011282 treatment Methods 0.000 claims description 64
- 238000001816 cooling Methods 0.000 claims description 48
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 37
- 239000010936 titanium Substances 0.000 claims description 30
- 229910052782 aluminium Inorganic materials 0.000 claims description 28
- 238000010438 heat treatment Methods 0.000 claims description 28
- 229910052719 titanium Inorganic materials 0.000 claims description 28
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 27
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 27
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 22
- 239000010955 niobium Substances 0.000 claims description 19
- 229910052742 iron Inorganic materials 0.000 claims description 18
- 239000011159 matrix material Substances 0.000 claims description 17
- 238000005728 strengthening Methods 0.000 claims description 17
- 229910052758 niobium Inorganic materials 0.000 claims description 15
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 15
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 13
- 229910052750 molybdenum Inorganic materials 0.000 claims description 13
- 239000011733 molybdenum Substances 0.000 claims description 13
- 238000001556 precipitation Methods 0.000 claims description 12
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 12
- 229910052721 tungsten Inorganic materials 0.000 claims description 12
- 239000010937 tungsten Substances 0.000 claims description 12
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 8
- 239000011651 chromium Substances 0.000 claims description 8
- 229910017052 cobalt Inorganic materials 0.000 claims description 8
- 239000010941 cobalt Substances 0.000 claims description 8
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 8
- 239000000203 mixture Substances 0.000 claims description 8
- 229910052759 nickel Inorganic materials 0.000 claims description 8
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 7
- 229910052804 chromium Inorganic materials 0.000 claims description 7
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 claims description 6
- 229910052796 boron Inorganic materials 0.000 claims description 6
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 229910052698 phosphorus Inorganic materials 0.000 claims description 6
- 239000011574 phosphorus Substances 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 abstract description 11
- 238000012360 testing method Methods 0.000 description 30
- 230000015572 biosynthetic process Effects 0.000 description 12
- 238000004881 precipitation hardening Methods 0.000 description 7
- 230000009467 reduction Effects 0.000 description 7
- 230000008569 process Effects 0.000 description 6
- 238000005275 alloying Methods 0.000 description 5
- 239000013078 crystal Substances 0.000 description 5
- 238000011161 development Methods 0.000 description 5
- 230000018109 developmental process Effects 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 238000002844 melting Methods 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 238000007792 addition Methods 0.000 description 3
- 229910001566 austenite Inorganic materials 0.000 description 3
- 230000007423 decrease Effects 0.000 description 3
- 238000000879 optical micrograph Methods 0.000 description 3
- 230000000717 retained effect Effects 0.000 description 3
- 238000001878 scanning electron micrograph Methods 0.000 description 3
- 230000003247 decreasing effect Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000035945 sensitivity Effects 0.000 description 2
- 238000009864 tensile test Methods 0.000 description 2
- 229910001247 waspaloy Inorganic materials 0.000 description 2
- 238000012935 Averaging Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- RKTYLMNFRDHKIL-UHFFFAOYSA-N copper;5,10,15,20-tetraphenylporphyrin-22,24-diide Chemical compound [Cu+2].C1=CC(C(=C2C=CC([N-]2)=C(C=2C=CC=CC=2)C=2C=CC(N=2)=C(C=2C=CC=CC=2)C2=CC=C3[N-]2)C=2C=CC=CC=2)=NC1=C3C1=CC=CC=C1 RKTYLMNFRDHKIL-UHFFFAOYSA-N 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- -1 i.e. Substances 0.000 description 1
- 238000009863 impact test Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000001000 micrograph Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000012768 molten material Substances 0.000 description 1
- 230000006911 nucleation Effects 0.000 description 1
- 238000010899 nucleation Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000002893 slag Substances 0.000 description 1
- 239000001632 sodium acetate Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- 238000010313 vacuum arc remelting Methods 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
Abstract
Embodiments of the present invention relate to nickel-base alloys, and in particular 718-type nickel-base alloys, having a desired microstructure that is predominantly strengthened by γ′-phase precipitates and comprises an amount of at least one grain boundary precipitate. Other embodiments of the present invention relate to methods of heat treating nickel-base alloys, and in particular 718-type nickel-base alloys, to develop a desired microstructure that can impart thermally stable mechanical properties. Articles of manufacture using the nickel-base alloys and methods of heat treating nickel-base alloys according to embodiments of the present invention are also disclosed.
Description
This is a continuation of application Ser. No. 10/679,899, filed Oct. 6, 2003, now U.S. Pat. No. 7,156,932.
Not applicable.
Not applicable.
1. Field of the Invention
Embodiments of the present invention generally relate to nickel-base alloys and methods of heat treating nickel-base alloys. More specifically, certain embodiments of the present invention relate to nickel-base alloys having a desired microstructure and having thermally stable mechanical properties (such as one or more of tensile strength, yield strength, elongation, stress-rupture life, and low notch sensitivity). Other embodiments of the present invention relate to methods of heat treating nickel-base alloys to develop a desired microstructure that can impart thermally stable mechanical properties at elevated temperatures, especially tensile strength, stress-rupture life, and low notch-sensitivity, to the alloys.
2. Description of Related Art
Alloy 718 is one of the most widely used nickel-base alloys, and is described generally in U.S. Pat. No. 3,046,108, the specification of which is specifically incorporated by reference herein.
The extensive use of Alloy 718 stems from several unique features of the alloy. For example, Alloy 718 has high strength and stress-rupture properties up to about 1200° F. Additionally, Alloy 718 has good processing characteristics, such as castability and hot-workability, as well as good weldability. These characteristics permit components made from Alloy 718 to be easily fabricated and, when necessary, repaired. As discussed below, Alloy 718's unique features stem from a precipitation-hardened microstructure that is predominantly strengthened by γ″-phase precipitates.
In precipitation-hardened, nickel-base alloys, there are two principal strengthening phases: γ′-phase (or “gamma prime”) precipitates and γ″-phase (or “gamma double prime”) precipitates. Both the γ′-phase and the γ″-phase are stoichiometric, nickel-rich intermetallic compounds. However, the γ′-phase typically comprises aluminum and titanium as the major alloying elements, i.e., Ni3(Al, Ti); while the γ″-phase contains primarily niobium, i.e., Ni3Nb. While both the γ′-phase and the γ″-phase form coherent precipitates in the face centered cubic austenite matrix, because there is a larger misfit strain energy associated with the γ″-phase precipitates (which have a body centered tetragonal crystal structure) than with the γ′-phase precipitates (which have a face centered cubic crystal structure), γ″-phase precipitates tend to be more efficient strengtheners than γ′-phase precipitates. That is, for the same precipitate volume fraction and particle size, nickel-base alloys strengthened by γ″-phase precipitates are generally stronger than nickel alloys that are strengthened primarily by γ′-phase precipitates.
However, one disadvantage to such a γ″-phase precipitate strengthened microstructure is that at temperatures higher than 1200° F., the γ″-phase is unstable and will transform into the more stable δ-phase (or “delta-phase”). While δ-phase precipitates have the same composition as γ″-phase precipitates (i.e., Ni3Nb), δ-phase precipitates have an orthorhombic crystal structure and are incoherent with the austenite matrix. Accordingly, the strengthening effect of δ-phase precipitates on the matrix is generally considered to be negligible. Therefore, as a result of this transformation, the mechanical properties of Alloy 718, such as stress-rupture life, deteriorate rapidly at temperatures above 1200° F. Therefore, the use of Alloy 718 typically is limited to applications below this temperature.
In order to form the desired precipitation-hardened microstructure, the nickel-base alloys must be subjected to a heat treatment or precipitation hardening process. The precipitation hardening process for a nickel-base alloy generally involves solution treating the alloy by heating the alloy at a temperature sufficient to dissolve substantially all of the γ′-phase and γ″-phase precipitates that exist in the alloy (i.e., a temperature near, at or above the solvus temperature of the precipitates), cooling the alloy from the solution treating temperature, and subsequently aging the alloy in one or more aging steps. Aging is conducted at temperatures below the solvus temperature of the gamma precipitates in order to permit the desired precipitates to develop in a controlled manner.
The development of the desired microstructure in the nickel-base alloy depends upon both the alloy composition and precipitation hardening process (i.e., the solution treating and aging processes) employed. For example, a typical precipitation hardening procedure for Alloy 718 for high temperature service involves solution treating the alloy at a temperature of 1750° F. for 1 to 2 hours, air cooling the alloy, followed by aging the alloy in a two-step aging process. The first aging step involves heating the alloy at a first aging temperature of 1325° F. for 8 hours, cooling the alloy at about 50 to 100° F. per hour to a second aging temperature of 1150° F., and aging the alloy at the second aging temperature for 8 hours. Thereafter, the alloy is air cooled to room temperature. The precipitation-hardened microstructure that results after the above-described heat treatment is comprised of discrete γ′ and γ″-phase precipitates, but is predominantly strengthened by the γ″-phase precipitates with minor amounts of the γ′-phase precipitates playing a secondary strengthening role.
Due to the foregoing limitations, many attempts have been made to improve upon Alloy 718. For example, modified Alloy 718 compositions that have controlled aluminum, titanium, and niobium alloying additions have been developed in order to improve the high temperature stability of the mechanical properties of the alloy. In particular, these alloys were developed in order to promote the development of a “compact morphology” microstructure during the precipitation hardening process. The compact morphology microstructure consists of large, cubic γ′-phase precipitates with γ″-phase precipitates being formed on the faces of the cubic γ′-phase precipitates. In other words, the γ″-phase forms a shell around the γ′-phase precipitates.
In addition to modified chemistry, a specialized heat treatment or precipitation hardening process is necessary to achieve the compact morphology microstructure, instead of the discrete γ′-phase and γ″-phase precipitate hardened microstructure previously discussed. One example of a specialized heat treatment that is useful in developing the compact morphology microstructure involves solution treating the alloy at a temperature around 1800° F., air cooling the alloy, and subsequently aging the alloy at a first aging temperature of approximately 1562° F. for about a half an hour, in order to precipitate coarse γ′-phase precipitates. After aging at the first aging temperature, the alloy is rapidly cooled to a second aging temperature by air cooling, and held at the second aging temperature, which is around 1200° F., for about 16 hours in order to form the γ″-phase shell. Thereafter, the alloy is air cooled to room temperature. As previously discussed, after this precipitation hardening process, the alloy will have the compact morphology microstructure described above and will have improved high temperature stability. However, the tensile strength of alloys having the compact morphology microstructure is generally significantly lower than for standard Alloy 718.
Many γ′-phase strengthened nickel-base alloys exist, for example, Waspaloy® nickel alloy, which is commercially available from Allvac of Monroe, N.C. However, because Waspaloy® nickel alloy contains increased levels of alloying additions as compared to Alloy 718, such as nickel, cobalt, and molybdenum, this alloy tends to be more expensive than Alloy 718. Further, because of the relatively fast precipitation kinetics of the γ′-phase precipitates as compared to the γ″-phase precipitates, the hot workability and weldability of this alloy is generally considered to be inferior to Alloy 718.
Accordingly, it would be desirable to develop an affordable, precipitation-hardened 718-type nickel-base alloy having a microstructure that is predominantly strengthened by the more thermally stable γ′-phase precipitates, that possesses thermally stable mechanical properties at temperatures greater than 1200° F., and that has comparable hot-workability and weldability to γ″-phase strengthened alloys. Further, it is desirable to develop methods of heat treating nickel-base alloys to develop a microstructure that is predominantly strengthened by thermally stable γ′-phase precipitates and that can provide nickel-base alloys with thermally stable mechanical properties and comparable hot-workability and weldability to γ″-phase strengthened
Certain embodiments of the present invention are directed toward methods of heat treating nickel-base alloys. For example, according to one non-limiting embodiment there is provided a method of heat treating a nickel-base alloy comprising pre-solution treating the nickel-base alloy wherein an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates is formed within the nickel-base alloy, the at least one grain boundary precipitate having a short, generally rod-shaped morphology; solution treating the nickel-base alloy wherein substantially all γ′-phase precipitates and γ″-phase precipitates in the nickel-base alloy are dissolved while at least a portion of the amount of the at least one grain boundary precipitate is retained; cooling the nickel-base alloy after solution treating the nickel-base alloy at a first cooling rate sufficient to suppress formation of γ′-phase and γ″-phase precipitates in the nickel-base alloy; aging the nickel-base alloy in a first aging treatment wherein primary precipitates of γ′-phase and γ″-phase are formed in the nickel-base alloy; and aging the nickel-base alloy in a second aging treatment wherein secondary precipitates of γ′-phase and γ″-phase are formed in the nickel-base alloy, the secondary precipitates being finer than the primary precipitates; and wherein after heat treating the γ′-phase precipitates are predominant strengthening precipitates in the nickel-base alloy.
According to another non-limiting embodiment there is provided a method of heat treating a 718-type nickel-base alloy, the nickel-base alloy including up to 14 weight percent iron, the method comprising pre-solution treating the nickel-base alloy at a temperature ranging from 1500° F. to 1650° F. for a time ranging from 2 to 16 hours, solution treating the nickel-base alloy for no greater than 4 hours at a solution temperature ranging from 1725° F. to 1850° F.; cooling the nickel-base alloy at a first cooling rate of at least 800° F. per hour after solution treating the nickel-base alloy; aging the nickel-base alloy in a first aging treatment for no greater than 8 hours at a temperature ranging from 1325° F. to 1450° F.; and aging the nickel-base alloy in a second aging treatment at least 8 hours at a second aging temperature, the second aging temperature ranging from 1150° F. to 1300° F.
Still another non-limiting embodiment provides a method of heat treating a nickel-base alloy, the nickel-base alloy comprising, in weight percent, up to 0.1 carbon, from 12 to 20 chromium, up to 4 molybdenum, up to 6 tungsten, from 5 to 12 cobalt, up to 14 iron, from 4 to 8 niobium, from 0.6 to 2.6 aluminum, from 0.4 to 1.4 titanium, from 0.003 to 0.03 phosphorus, from 0.003 to 0.015 boron, and nickel; wherein a sum of the weight percent of molybdenum and the weight percent of tungsten is at least 2 and not more than 8, and wherein a sum of atomic percent aluminum and atomic percent titanium is from 2 to 6, a ratio of atomic percent aluminum to atomic percent titanium is at least 1.5, and the sum of atomic percent aluminum and atomic percent titanium divided by atomic percent niobium is from 0.8 to 1.3. The method comprises solution treating the nickel-base alloy for no greater than 4 hours at a solution temperature ranging from 1725° F. to 1850° F.; cooling the nickel-base alloy at a first cooling rate after solution treating the nickel-base alloy; aging the solution treated nickel-base alloy in a first aging treatment for no greater than 8 hours at a temperature ranging from 1365° F. to 1450° F.; and aging the nickel-base alloy in a second aging treatment for at least 8 hours at a second aging temperature, the second aging temperature ranging from 1150° F. to 1300° F.
Other embodiments of the present invention contemplate nickel-base alloys having a desired microstructure. For example, in one non-limiting embodiment there is provided a nickel-base alloy comprising a matrix comprising γ′-phase precipitates and γ″-phase precipitates, wherein the γ′-phase precipitates are predominant strengthening precipitates in the nickel-base alloy, and an amount of a at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates, wherein the at least one grain boundary precipitate has a short, generally rod-shaped morphology; and wherein the nickel-base alloy has a yield strength at 1300° F. of at least 120 ksi, a percent elongation at 1300° F. of at least 12 percent, a notched stress-rupture life of at least 300 hours as measured at 1300° F. and 80 ksi, and a low notch-sensitivity.
Another non-limiting embodiment provides a 718-type nickel-base alloy including up to 14 weight percent iron and comprising γ′-phase precipitates and γ″-phase precipitates, wherein the γ′-phase precipitates are the predominant strengthening precipitates in the nickel-base alloy, and an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates, wherein the at least one grain boundary precipitate has a short, generally rod-shaped morphology; wherein the nickel-base alloy is heat treated by pre-solution treating the nickel-base alloy at a temperature ranging from 1500° F. to 1650° F. for a time ranging from 2 to 16 hours; solution treating the nickel-base alloy by heating the nickel-base alloy for no greater than 4 hours at a solution temperature ranging from 1725° F. to 1850° F.; cooling the nickel-base alloy at a first cooling rate of at least 800° F. per hour after solution treating the nickel-base alloy; aging the nickel-base alloy in a first aging treatment from 2 hours to 8 hours at a temperature ranging from 1325° F. to 1450° F.; and aging the nickel-base alloy in a second aging treatment for at least 8 hours at a second aging temperature, the second aging temperature ranging from 1150° F. to 1300° F.
Articles of manufacture and methods of forming article of manufacture are also contemplated by various embodiments of the present invention. For example, there is provided in one non-limiting embodiment of the present invention, an article of manufacture comprising a nickel-base alloy, the nickel-base alloy comprising a matrix comprising γ′-phase precipitates and γ″-phase precipitates, wherein the γ′-phase precipitates are predominant strengthening precipitates in the nickel-base alloy, and an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates, wherein the at least one grain boundary precipitates has a short, generally rod-shaped morphology; and wherein the nickel-base alloy has a yield strength at 1300° F. of at least 120 ksi, a percent elongation at 1300° F. of at least 12 percent, a notched stress-rupture life of at least 300 hours as measured at 1300° F. and 80 ksi, and a low notch-sensitivity.
Another non-limiting embodiment provides a method of forming an article of manufacture comprising a 718-type nickel-base alloy including up to 14 weight percent iron, the method comprising forming the nickel-base alloy into a desired configuration, and heat treating the nickel-base alloy, wherein heat treating the nickel-base alloy comprises pre-solution treating the nickel-base alloy at a temperature ranging from 1500° F. to 1650° F. for a time ranging from 2 to 16 hours, solution treating the nickel-base alloy for no greater than 4 hours at a solution temperature ranging from 1725° F. to 1850° F., cooling the nickel-base alloy at a first cooling rate of at least 800° F. per hour after solution treating the nickel-base alloy, aging the nickel-base alloy in a first aging treatment from 2 hours to 8 hours at a temperature ranging from 1325° F. to 1450° F., and aging the nickel-base alloy in a second aging treatment for at least 8 hours at a second aging temperature, the second aging temperature ranging from 1150° F. to 1300° F.
Embodiments of the present invention will be better understood if read in conjunction with the figures, in which:
Certain non-limiting embodiments of the present invention can be advantageous in providing nickel-base alloys having a desired microstructure and thermally stable mechanical properties at elevated temperatures. As used herein, the phrase “thermally stable mechanical properties” means that the mechanical properties of the alloy (such as tensile strength, yield strength, elongation, and stress-rupture life) are not substantially decreased after exposure at 1400° F. for 100 hours as compared to the same mechanical properties before exposure. As used herein the term “low notch-sensitivity” means that samples of the alloy, when tested according to ASTM E292, do not fail at the notch. Further, the non-limiting embodiments of the present invention may be advantageous in providing predominantly γ′-phase strengthened nickel-base alloys comprising at least one grain boundary phase precipitate and having comparable hot-workability and weldability to γ″-phase strengthened alloys.
Methods of heat treating nickel-base alloys according to various non-limiting embodiments of the present invention will now be described. Although not limiting herein, the methods of heat treating nickel-base alloys discussed herein can be used in conjunction with a variety of nickel-base alloy compositions, and are particularly suited for use with 718-type nickel-base alloys and derivatives thereof. As used herein the term “nickel-base alloy(s)” means alloys of nickel and one or more alloying elements. As used herein the term “718-type nickel-base alloy(s)” means nickel-base alloys comprising chromium and iron that are strengthened by one or more of niobium, aluminum, and titanium alloying additions.
One specific, non-limiting example of a 718-type nickel-base alloy for which the heat treating methods of the various non-limiting embodiments of the present invention are particularly well suited is a 718-type nickel-base alloy including up to 14 weight percent iron. Although not meant to be limiting herein, 718-type nickel-base alloys including up to 14 weight percent iron are believed to be advantageous in producing alloys having good stress-rupture life. While not intending to be bound by any particular theory, it is believed by the inventors that when the iron content of the alloy is high, for example 18 weight percent, the effectiveness of cobalt in lowering stacking fault energy may be reduced. Since low stacking fault energies are associated with improved stress-rupture life, in certain embodiments of the present invention, the iron content of the nickel-base alloy is desirably maintained at or below 14 weight percent.
Another specific, non-limiting example of a 718-type nickel-base alloy for which the heat treating methods according to the various non-limiting embodiments of the present invention are particularly well suited is a nickel-base alloy comprising, in percent by weight, up to 0.1 carbon, from 12 to 20 chromium, up to 4 molybdenum, up to 6 tungsten, from 5 to 12 cobalt, up to 14 iron, from 4 to 8 niobium, from 0.6 to 2.6 aluminum, from 0.4 to 1.4 titanium, from 0.003 to 0.03 phosphorus, from 0.003 to 0.015 boron, and nickel; wherein a sum of the weight percent of molybdenum and the weight percent of tungsten is at least 2 and not more than 8, and wherein a sum of atomic percent aluminum and atomic percent titanium is from 2 to 6, a ratio of atomic percent aluminum to atomic percent titanium is at least 1.5, and the sum of atomic percent aluminum and atomic percent titanium divided by atomic percent niobium is from 0.8 to 1.3. Such alloys are described in detail in co-pending U.S. application Ser. No. 10/144,369, the specification of which is specifically incorporated by reference herein.
A method of heat treating a nickel-base alloy according to a first, non-limiting embodiment of the present invention comprises pre-solution treating the nickel-base alloy, solution treating the nickel-base alloy, and aging the nickel-base alloy to form a nickel-base alloy having a microstructure wherein γ′-phase precipitates are the predominant strengthening precipitates and δ-phase and/or η-phase precipitates having a desired morphology are present in one or more of the grain boundaries of the alloy.
More specifically, the method of heat treating a nickel-base alloy according to the first non-limiting embodiment comprises pre-solution treating the nickel-base alloy wherein an amount of at least one grain boundary precipitate is formed within the nickel-base alloy. As used herein the term “pre-solution treating” means heating the nickel-base alloy, prior to solution treating the nickel-base alloy, at a temperature such that an amount of at least one grain boundary precipitate is formed within the nickel-base alloy. As used herein, the term “form” with respect to any phase means nucleation and/or growth of the phase. For example, although not limiting herein, pre-solution treating the nickel-base alloy can comprise heating the nickel-base alloy in a furnace at a temperature ranging from about 1500° F. to about 1650° F. for about 2 hours to about 16 hours. In one specific, non-limiting example of a pre-solution treatment that can be particularly useful in processing wrought nickel-base alloys, the pre-solution treatment can comprise heating the alloy at a temperature ranging from about 1550° F. to 1600° F. for about 4 to 16 hours.
As discussed above, during the pre-solution treatment, an amount of at least one grain boundary precipitate is formed in the nickel-base alloy. According to the first non-limiting embodiment, the at least one grain boundary precipitate formed during the pre-solution treatment is selected from the group consisting of δ-phase (“delta-phase”) precipitates and η-phase (“eta-phase”) precipitates. Delta-phase precipitates are known in the art to consist of the ordered intermetallic phase Ni3Nb and have an orthorhombic crystal structure. Eta-phase precipitates are known in the art to consist of the ordered intermetallic phase Ni3Ti and have a hexagonal crystal structure. Further, according to this embodiment, during pre-solution treatment both δ-phase and η-phase grain boundary precipitates can be formed.
While generally the formation of δ-phase and/or η-phase precipitates (hereinafter “δ/η-phase” precipitates) in nickel-base alloys due to the averaging of γ″-phase precipitates is undesirable because these precipitates are incoherent and do not contribute to the strengthening of the austenite matrix, the inventors have observed that the precipitation of a controlled amount of δ/η-phase precipitates having a desired morphology and location in grain boundaries of the nickel-base alloy (as discussed in more detail below) can strengthen the grain boundaries and contribute to reduced notch-sensitivity, and improved stress-rupture life and ductility in the alloy at elevated temperatures. Further, as discussed below in more detail, when the controlled amount of at least one grain boundary precipitate is combined with γ′-phase and γ″-phase precipitates having the desired size distribution, nickel-base alloys having low notch-sensitivity, good tensile strength, stress-rupture life, and thermally stable mechanical properties to at least 1300° F. can be achieved.
Referring now to the figures, in FIG. 1 , there is shown an SEM micrograph of a nickel-base alloy according to embodiments of the present invention taken at 3000× magnification. In FIG. 2 there is shown an optical micrograph of the same nickel-base alloy taken at 500× magnification. The nickel-base alloy shown in FIGS. 1 and 2 comprises an amount of at least one grain boundary precipitate having the desired morphology and location according to certain non-limiting embodiments of the present invention. As shown in FIG. 1 , the nickel-base alloy comprises δ/η-phase precipitates 110, the majority of which have a short, generally rod-shaped morphology and are located within the grain boundaries of the alloy. As used herein the phrase “short, generally rod-shaped” with reference to the precipitates means the precipitates having a length to thickness aspect ratio no greater than about 20, for example as shown in FIGS. 1 and 2 . In certain non-limiting embodiments of the present invention, the aspect ratio of the short, generally rod-shaped precipitates ranges from 1 to 20. While δ/η-phase precipitates at twin boundaries in the nickel-base alloy can occasionally be present (for example, as shown in FIG. 1 , δ/η-phase precipitates 111 can be observed at twin boundary 121), no significant formation of intragranular, needle-shaped δ/η-phase precipitates should be present in the nickel-base alloys processed in accordance with the various non-limiting embodiments of the present invention.
Although not meaning to be bound by any particular theory, it is believed by the inventors that both the morphology of the precipitates and location of precipitates at the grain boundaries, shown in FIGS. 1 and 2 , are desirable in providing a nickel-base alloy having low notch-sensitivity and improved tensile ductility and stress-rupture life because these grain boundary precipitates can restrict grain boundary sliding in the alloy at elevated temperatures. In other words, because of their morphology and location, the grain boundary precipitates according to embodiments of the present invention effectively strengthen the grain boundaries by resisting movement of the grain boundaries by “locking” or “pinning” the grain boundaries in place. Since grain boundary sliding contributes substantially to creep deformation and the formation of inter-granular cracks, which can decrease stress-rupture life and increase notch-sensitivity of the alloy, by restricting grain boundary sliding in the nickel-base alloys according to embodiments of the present invention, the grain boundary precipitates can increase the tensile ductility and stress-rupture life of the alloy and decrease the notch-sensitivity of the alloy. In contrast, when no grain boundary phase is present, or when excessive precipitation occurs (as shown in FIGS. 3 and 4 , which are discussed below), the grain boundaries will not be strengthened and the stress-rupture life of the alloy will not be improved.
In certain non-limiting embodiments of the present invention, after heat treating the nickel-base alloy a majority of grain boundaries of the nickel-base alloy are pinned by at least one short, generally rod-shaped grain boundary precipitate, such as precipitate 210 shown in FIG. 2 . In other embodiments of the present invention, at least two-thirds (⅔) of the grain boundaries are pinned by at least one short, generally rod-shaped grain boundary phase precipitate. Thus, according to these non-limiting embodiments, although pinning of all of the grain boundaries by at least one grain boundary precipitate is contemplated, it is not necessary that all of the grain boundaries be pinned.
In contrast, FIGS. 3 and 4 are micrographs of a nickel-base alloy having excessive formation of δ/η-phase precipitates. As shown in FIG. 3 , the majority of the precipitates 310 have a sharp, needle-like morphology with a much larger aspect ratio than those shown in FIGS. 1 and 2 , and extend a significant distance into the grains, and in some cases, extend across an individual grain. Although not meant to be bound by any particular theory, it is believed by the inventors that the δ/η-phase precipitate morphology and the location of the precipitates in the grains shown in FIGS. 3 and 4 is undesirable because the δ/η-phase precipitates (310 and 410, shown in FIGS. 3 and 4 respectively) do not strengthen the grain boundaries as discussed above. Instead, the interface between the precipitate and the grain matrix becomes the easiest path for crack propagation. Further, the excessive formation of δ/η-phase precipitates reduces the amount of strengthening precipitates (i.e., γ′ and γ″) in the alloy, thereby reducing the strength of the alloy (as previously discussed). Accordingly, although the precipitates such as those shown in FIGS. 3 and 4 can contribute to an increase in elevated temperature ductility, such precipitation will significantly reduce alloy tensile strength and stress-rupture life.
While not intending to be bound by any particular theory, the inventors have also observed that the morphology of δ/η-phase grain boundary precipitates is related to precipitation temperature and the grain size of the alloy. Thus, for example, although not limiting herein, for certain wrought alloys when the precipitation temperature is greater than about 1600° F., and for certain cast alloys when the precipitation temperature is greater than about 1650° F., generally the δ/η-phase precipitates will form both on grain boundaries and intragranularly as high aspect ratio needles. As discussed above, this typically decreases the tensile strength and stress-rupture life of the alloy. However, when precipitation of the δ/η-phase occurs in these alloys at temperatures below about 1600° F. and 1650° F., respectively, δ/η-phase precipitates having a relatively short, generally rod-shaped morphology form at the grain boundaries, with little intragranular precipitation. As previously discussed, the formation of these grain boundary precipitates in the nickel-base alloy is desirable because these grain boundary precipitates can lock or pin the grain boundaries, thereby improving the tensile strength and ductility, and stress-rupture life, while decreasing notch-sensitivity of the alloy.
After pre-solution treating, according to the first non-limiting embodiment of the present invention, the nickel-base alloy can be cooled to 1000° F. or less prior to solution treating. For example, although not limiting herein, the alloy can be cooled to room temperature prior to solution treating. As used herein, the term “solution treating” means heating the nickel-base alloy at a solution temperature near (i.e., a temperature no less than about 100° F. below), at or above the solvus temperature of the γ′ and γ″-phase precipitates, but below the solvus temperature for the grain boundary precipitates. Thus, as discussed above, during solution treatment of the nickel-base alloy, substantially all the γ′- and γ″-phase precipitates that exist in the nickel-base alloy are dissolved. As used herein, the term “substantially all” with respect to the dissolution of the γ′ and γ″-phase precipitates during solution treating means at least a majority of the γ′ and γ″-phase precipitates are dissolved. Accordingly, dissolving substantially all of the γ′- and γ″-phase precipitates during solution treating includes, but is not limited to, dissolving all of the γ′- and γ″-phase precipitates. However, since the solution temperature is below the solvus temperature for the grain boundary precipitates (i.e., the δ/η-phase precipitates formed during pre-solution treatment), at least a portion of the amount of the at least one grain boundary precipitate is retained in the nickel-base alloy during solution treatment.
Although not limiting herein, according to this non-limiting embodiment, solution treating the nickel-base alloy can comprise heating the nickel-base alloy at a solution temperature no greater than 1850° F. for no more than 4 hours. More particularly, solution treating the nickel-base alloy can comprise heating the nickel-base alloy at a solution temperature ranging from 1725° F. to 1850° F., and more preferably comprises heating the nickel-base alloy from 1750° F. to 1800° F. for a time ranging from 1 to 4 hours, and more preferably from 1 to 2 hours. However, it will be appreciated by those skilled in the art that the exact solution treatment time required to dissolve substantially all of the γ′- and γ″-phase precipitates will depend on several factors, including but not limited to, the size of the nickel-base alloy being solution treated. Thus, the bigger the nickel-base alloy (or work piece comprising the nickel-base alloy) being treated, generally the longer the solution time required to achieve the desired result will be.
Although not meaning to be bound by any particular theory, it has been observed by the inventors that if the solution temperature is above about 1850° F., a less than desired amount of grain boundary precipitates may be retained in the nickel-base alloy after solution treating. Accordingly, the notch-sensitivity, elevated temperature stress-rupture life and ductility of the alloy can be detrimentally affected. However, for applications in which these properties are not critical, solution temperatures greater than 1850° F. can be utilized in accordance with this non-limiting embodiment of the present invention. Further, it has been observed by the inventors that if the solution temperature is below about 1725° F., substantially all of the γ′-phase and γ″-phase precipitates will not dissolve during solution treatment. Accordingly, undesirable growth and coarsening of the undissolved γ′-phase and γ″-phase precipitates can occur, leading to lower tensile strength and stress-rupture life.
After solution treating the nickel-base alloy, the nickel-base alloy is cooled at a first cooling rate sufficient to suppress formation of γ′-phase and γ″-phase precipitates in the nickel-base alloy during cooling. Although not meant to be limiting herein, the inventors have observed that if the nickel-base alloy is cooled too slowly after solution treatment, in addition to the undesired precipitation and coarsening of γ′-phase and γ″-phase precipitates, the formation of excessive grain boundary precipitates can occur. As discussed above, the formation of excessive grain boundary precipitates can detrimentally impact the tensile strength and stress-rupture life of the alloy. Thus, according to the first non-limiting embodiment of the present invention, the first cooling rate is at least 800° F. per hour, and can be at least 1000° F. per hour or greater. Cooling rates in excess of 800° F. or 1000° F. can be achieved, for example by air cooling the alloys from the solution temperature.
After solution treating and cooling the nickel-base alloy according to the first non-limiting embodiment of the present invention, the nickel-base alloy is aged in a first aging treatment. As used herein the term “aging” means heating the nickel-base alloy at a temperature below the solvus temperatures for the γ′-phase and the γ″-phase to form γ′-phase and γ″-phase precipitates. During the first aging treatment, primary precipitates of γ′-phase and γ″-phase are formed in the nickel-base alloy. Although not limiting herein, according to this non-limiting embodiment, the first aging treatment can comprise heating the nickel-base alloy at temperatures ranging from 1325° F. to 1450° F. for a time period ranging from 2 to 8 hours. More particularly, the first aging treatment can comprise heating the nickel-base alloy at a temperature ranging from 1365° F. to 1450° F. for 2 to 8 hours. Although not meant to be limiting herein, aging at a first aging temperature greater than about 1450° F. or less than about 1325° F. can result in overaging or underaging of the alloy, respectively, with an accompanying loss of strength.
After the first aging treatment, the nickel-base alloy is cooled to a second aging temperature and aged in a second aging treatment. Although not required, according to this embodiment of the present invention the second cooling rate can be 50° F. per hour or greater. For example, a cooling rate ranging from about 50° F. per hour to about 100° F. per hour can be achieved by allowing the nickel-base alloy to cool in the furnace while the furnace cools to a desired temperature or after the power to the furnace is turned off (i.e., furnace cooling the alloy). Alternatively, although not limiting herein, the nickel-base alloy can be more rapidly cooled, for example by air cooling to room temperature, and then subsequently heated to the second aging temperature. However, if a more rapid cooling rate is employed, longer aging times may be required in order to develop the desired microstructure.
The nickel-base alloy is aged at the second aging temperature to form secondary precipitates of γ′-phase and γ″-phase in the nickel-base alloy. The secondary precipitates of γ′-phase and γ″-phase formed during the second aging treatment are generally finer than the primary precipitates formed during the first aging treatment. That is, the size of the precipitates formed during the second aging treatment will generally be smaller than the size of the primary precipitates formed during the first aging treatment. Although not meaning to be bound by any particular theory, the formation of γ′-phase precipitates and γ″-phase precipitates having a distribution of sizes, as opposed to a uniform precipitate size, is believed to improve the mechanical properties of the nickel-base alloy.
Further, according to the first non-limiting embodiment, the second aging treatment can comprise heating the nickel-base alloy at a second aging temperature ranging from 1150° F. to 1300° F., and more specifically can comprise heating the nickel-base alloy at a second aging temperature ranging from 1150° F. to 1200° F. for at least 8 hours.
As previously discussed, after heat treating the nickel-base alloy according to the first non-limiting embodiment of the present invention, the γ′-phase precipitates are predominant strengthening precipitates in the nickel-base alloy. As used herein, the phrase “predominant strengthening precipitates” with respect to the γ′-phase precipitates means the nickel-base alloy comprises at least about 20 volume percent γ′-phase and no more than about 5 volume percent γ″-phase. Further, after heat treating, the nickel-base alloy according to this non-limiting embodiment comprises an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates and having a short, generally rod-shaped morphology.
In a second non-limiting embodiment of the present invention, the nickel-base alloy is heated to a pre-solution temperature ranging from about 1500° F. to 1600° F. for a period of time in order to precipitate a controlled amount of at least one grain boundary precipitate selected from the group consisting of γ-phase precipitates and η-phase precipitates. As discussed above with respect to the first non-limiting embodiment, desirably, the at least one precipitate has a short, generally rod-shaped morphology and is located at the grain boundaries of the alloy.
Thereafter, the temperature is increased to a solution temperature ranging from 1725° F. to about 1850° F., without cooling, and the nickel-base alloy is solution treated (i.e., the alloy is directly heated to the solution temperature). The nickel-base alloy is held at the solution temperature for a time period sufficient to dissolve substantially all of the γ′-phase and γ″-phase precipitates as discussed above. For example, although not limiting herein, the nickel-base alloy can be held at the solution temperature for no greater than 4 hours. In one specific, non-limiting example according to the second non-limiting embodiment, the solution temperature ranges from 1750° F. to about 1800° F. and the alloy is held at the solution temperature for no greater than 2 hours. Thereafter, the nickel-base alloy can be cooled to room temperature and aged as discussed above with respect to the first non-limiting embodiment of the present invention.
A third non-limiting embodiment of the present invention provides a method of heat treating a 718-type nickel-base alloy including up to 14 weight percent iron, the method comprising pre-solution treating the nickel-base alloy at a temperature ranging from 1500° F. to 1650° F. for a time ranging from 2 to 16 hours. After pre-solution treatment, the nickel-base alloy is solution treated for no greater than 4 hours at a solution temperature ranging from 1725° F. to 1850° F., and preferably for no greater than 2 hours at a solution temperature ranging from 1750° F. to 1800° F. Thereafter, the nickel-base alloy can be cooled to room temperature and aged as discussed above with respect to the first non-limiting embodiment of the present invention. After heat treating the nickel-base alloy according to this non-limiting embodiment of the present invention, the nickel-base alloy desirably has a microstructure comprising γ′-phase precipitates and γ″-phase precipitates, wherein the γ′-phase precipitates are predominant strengthening precipitates in the nickel-base alloy, and an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates, the at least one grain boundary precipitate having a short, generally rod-shaped morphology.
A fourth non-limiting embodiment according to the present invention provides a method of heat treating a nickel-base alloy, the nickel-base alloy comprising, in weight percent, up to 0.1 carbon, from 12 to 20 chromium, up to 4 molybdenum, up to 6 tungsten, from 5 to 12 cobalt, up to 14 iron, from 4 to 8 niobium, from 0.6 to 2.6 aluminum, from 0.4 to 1.4 titanium, from 0.003 to 0.03 phosphorus, from 0.003 to 0.015 boron, and nickel; wherein a sum of the weight percent of molybdenum and the weight percent of tungsten is at least 2 and not more than 8, and wherein a sum of atomic percent aluminum and atomic percent titanium is from 2 to 6, a ratio of atomic percent aluminum to atomic percent titanium is at least 1.5, and the sum of atomic percent aluminum and atomic percent titanium divided by atomic percent niobium is from 0.8 to 1.3. The method comprises solution treating the nickel-base alloy by heating the nickel-base alloy for no greater than 4 hours at a solution temperature ranging from 1725° F. to 1850° F., and more particularly comprises solution treating the nickel-base alloy by heating the nickel-base alloy for not greater than 2 hours at a solution temperature ranging from 1750° F. to 1800° F. The method further comprises cooling the nickel-base alloy after solution treating at a first cooling rate, and aging the nickel-base alloy as discussed above with respect to the first non-limiting embodiment of the present invention. After heat treating the nickel-base alloy according to the fourth non-limiting embodiment of the present invention, the nickel-base alloy desirably has a microstructure that is predominantly strengthened by γ′-phase precipitates and may comprise an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates, the at least one grain boundary precipitate having a short, generally rod-shaped morphology.
Although not required, the method according to the fourth non-limiting embodiment of the present invention can further comprise pre-solution treating the nickel-base alloy at a temperature ranging from 1500° F. to 1650° F. for a time period ranging from 2 to 16 hours prior to solution treating the nickel-base alloy. As previously discussed, by pre-solution treating the nickel-base alloy, a controlled amount of at least one grain boundary precipitate can be formed in the alloy. Accordingly, after heat treating the nickel-base alloy, the nickel-base alloy desirably has a microstructure that is primarily strengthened by γ′-phase precipitates and comprises an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates, wherein the at least one grain boundary precipitate has a short, generally rod-shaped morphology.
Although not limiting herein, after heat treating the nickel-base alloy according to the various non-limiting embodiments of the present invention discussed above, the nickel-base alloy can have a yield strength at 1300° F. of at least 120 ksi, a percent elongation at 1300° F. of at least 12 percent, a notched stress-rupture life of at least 300 hours as measured at 1300° F. and 80 ksi, and a low notch-sensitivity. Although not required, after heat treating the alloy can have a grain size of ASTM 5-8.
Nickel-base alloys having a desired microstructure according to certain non-limiting embodiments of the present invention will now be discussed. In one non-limiting embodiment of the present invention, there is provided a nickel-base alloy comprising a matrix comprising γ′-phase precipitates and γ″-phase precipitates, wherein the γ′-phase precipitates are predominant strengthening precipitates in the nickel-base alloy, and a controlled amount of at least one grain boundary precipitate, the at least one grain boundary precipitate being selected from the group consisting of δ-phase precipitates and η-phase precipitates; and wherein the nickel-base alloy has a yield strength at 1300° F. of at least 120 ksi, a percent elongation at 1300° F. of at least 12 percent, a notched stress-rupture life of at least 300 hours as measured at 1300° F. and 80 ksi, and a low notch-sensitivity.
According to this non-limiting embodiment, the nickel-base alloy can be a 718-type nickel-base alloy. For example, the 718-type nickel-base alloy can be a 718-type nickel-base alloy comprising up to 14 weight percent iron. Further, the 718-type nickel-base alloy can be a nickel-base alloy comprising, in weight percent, up to 0.1 carbon, from 12 to 20 chromium, up to 4 molybdenum, up to 6 tungsten, from 5 to 12 cobalt, up to 14 iron, from 4 to 8 niobium, from 0.6 to 2.6 aluminum, from 0.4 to 1.4 titanium, from 0.003 to 0.03 phosphorus, from 0.003 to 0.015 boron, and nickel; wherein a sum of the weight percent of molybdenum and the weight percent of tungsten is at least 2 and not more than 8, and wherein a sum of atomic percent aluminum and atomic percent titanium is from 2 to 6, a ratio of atomic percent aluminum to atomic percent titanium is at least 1.5, and the sum of atomic percent aluminum and atomic percent titanium divided by atomic percent niobium is from 0.8 to 1.3.
The nickel-base alloy according to this non-limiting embodiment can be a cast or wrought nickel-base alloy. For example, although not limiting herein, the nickel-base alloy can be manufactured by melting raw materials having the desired composition in a vacuum induction melting (“VIM”) operation, and subsequently casting the molten material into an ingot. Thereafter, the cast material can be further refined by remelting the ingot. For example, the cast material can be remelted via vacuum arc remelting (“VAR”), electro-slag remelting (“ESR”), or a combination of ESR and VAR, all of which are known in the art. Alternatively, other methods known in the art for melting and remelting can be utilized.
After melting, the nickel-base alloy can be heat treated to form the desired microstructure. For example, although not limiting herein, the nickel-base alloy can be heat treated according to the methods of heat treating discussed in the various non-limiting embodiments of the present invention discussed above to form the desired microstructure. Alternatively, the alloy can be first forged or hot or cold worked prior to heat treating.
One specific, non-limiting embodiment of a nickel-base alloy according to the present invention provides a 718-type nickel-base alloy including up to 14 weight percent iron and comprising γ′-phase precipitates and γ″-phase precipitates, wherein the γ′-phase precipitates are predominant strengthening precipitates in the nickel-base alloy, and an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates, the at least one grain boundary precipitate having a short, generally rod-shaped morphology. According to this non-limiting embodiment, the nickel-base alloy can be formed, for example, by pre-solution treating the nickel-base alloy by heating the nickel-base alloy at a temperature ranging from 1500° F. to 1650° F. for a time ranging from 4 to 16 hours, solution treating the nickel-base alloy by heating the nickel-base alloy for no greater than 4 hours at a solution temperature ranging from 1725° F. to 1850° F., cooling the nickel-base alloy at a first cooling rate of at least 800° F. per hour after solution treating the nickel-base alloy, aging the nickel-base alloy in a first aging treatment by heating the nickel-base alloy for 2 to 8 hours at a temperature ranging from 1325° F. to 1450° F., and aging the nickel-base alloy in a second aging treatment by heating the nickel-base alloy for at least 8 hours at the second aging temperature, the second aging temperature ranging from 1150° F. to 1300° F.
Embodiments of the present invention further contemplate articles of manufacture made using the nickel-base alloys and methods of heat treating nickel-base alloys of the present invention. Non-limiting examples of articles of manufacture that can be made using the nickel-base alloys and methods of heat treating nickel-base alloys according to the various embodiments of the present invention include, but are not limited to, turbine or compressor disks, blades, cases, shafts, and fasteners.
For example, although not limiting herein, one embodiment of the present invention provides an article of manufacture comprising a nickel-base alloy, the nickel-base alloy comprising a matrix comprising γ′-phase precipitates and γ″-phase precipitates, wherein the γ′-phase precipitates are predominant strengthening precipitates in the nickel-base alloy, and an amount of at least one grain boundary precipitate selected from the group consisting of δ-phase precipitates and η-phase precipitates; and wherein the nickel-base alloy has a yield strength at 1300° F. of at least 120 ksi, a percent elongation at 1300° F. of at least 12 percent, a notched stress-rupture life of at least 300 hours as measured at 1300° F. and 80 ksi, and a low notch-sensitivity. Although not required, the nickel-base alloy can have a grain size of ASTM 5-8.
Although not limiting herein, the articles of manufacture according to this non-limiting embodiment of the present invention can be formed, for example, by forming a cast or wrought nickel-base alloy having the desired composition into the desired configuration, and then subsequently heat treating the nickel-base alloy to form the desired microstructure discussed above. More particularly, although not limiting herein, according to certain embodiments of the present invention the articles of manufacture can be formed from cast or wrought 718-type nickel-base alloys, and more particularly 718-type nickel-base alloys that include up to 14 weight percent iron. In one specific non-limiting embodiment of the present invention, the article of manufacture is formed from a nickel-base alloy comprising, in percent by weight, up to 0.1 carbon, from 12 to 20 chromium, up to 4 molybdenum, up to 6 tungsten, from 5 to 12 cobalt, up to 14 iron, from 4 to 8 niobium, from 0.6 to 2.6 aluminum, from 0.4 to 1.4 titanium, from 0.003 to 0.03 phosphorus, from 0.003 to 0.015 boron, and nickel; wherein a sum of the weight percent of molybdenum and the weight percent of tungsten is at least 2 and not more than 8, and wherein a sum of atomic percent aluminum and atomic percent titanium is from 2 to 6, a ratio of atomic percent aluminum to atomic percent titanium is at least 1.5, and the sum of atomic percent aluminum and atomic percent titanium divided by atomic percent niobium is from 0.8 to 1.3.
Various non-limiting embodiments of the present invention will now be illustrated in the following non-limiting examples.
A 718-type nickel-base alloy was melted prepared using in a VIM operation and subsequently cast into an ingot. Thereafter, the cast material was remelted using VAR. The cast material was then forged into an 8″ diameter, round billet and test samples were cut the billet. The alloy had a grain size ranging from ASTM 6 to ASTM 8, with an average grain size of ASTM 7, as determined according to ASTM E 112, as determined according to ASTM E 112. The composition of alloy is given below.
| Element | Weight Percent | ||
| C | 0.028 | ||
| W | 1.04 | ||
| Co | 9.17 | ||
| Nb | 5.50 | ||
| Al | 1.47 | ||
| B | 0.005 | ||
| Mo | 2.72 | ||
| Cr | 17.46 | ||
| Fe | 9.70 | ||
| Ti | 0.71 | ||
| P | 0.014 | ||
| Ni + residual elements | Balance | ||
The test samples were then divided into sample groups and the sample groups were subjected the pre-solution treatment indicated below in Table 1.
| TABLE 1 | |
| Sample Group | Pre-solution Treatment |
| 1 | None |
| 2 | 1550° F. for 8 Hours |
| 3 | 1600° F. for 8 Hours |
| 4 | 1650° F. for 8 Hours |
After pre-solution treatment, each of the sample groups were solution treated at 1750° F. for 1 hour, air cooled, aged for 2 hours at 1450° F., furnace cooled, aged for 8 hours at 1200° F., and air cooled to room temperature. After heat treating the following tests were performed. At least 2 samples from each sample group were subjected to tensile testing at 1300° F. according to ASTM E21 and the tensile strength, yield strength, percent elongation, and percent reduction in area for each sample were determined. At least 2 samples from each sample group were subjected to stress-rupture life testing at 1300° F. and 80 ksi according to ASTM 292 and the stress-rupture life and percent elongation at rupture for each sample were determined. At least 2 samples from each group were subjected to Charpy testing at room temperature according to ASTM E262 and the impact strength and lateral expansion (“LE”) of each sample were determined.
The results of the aforementioned tests are indicated below in Table 2, wherein the tabled value is the average value of the samples tested from each sample group.
| TABLE 2 | ||||||||
| Tensile | Yield | Stress- | Impact | |||||
| Strength | Strength | Percent | Rupture | Percent | Strength | LE at | ||
| at | at | Percent | Reduction | Life at | Elongation | at Room | Room | |
| Sample | 1300° F. | 1300° F. | Elongation | in Area at | 1300° F. | at Rupture | Temp. | Temp |
| Group | (ksi) | (ksi) | at 1300° F. | 1300° F. | (Hours) | at 1300° F. | (Ft. lbs) | (mils) |
| 1 | 170.3 | 145.7 | 19.3 | 18.1 | 433.1 | 35.4 | 13.5 | 8.5 |
| 2 | 172.3 | 149.2 | 28.9 | 52.3 | 581.4 | 29.4 | 33.5 | 19.0 |
| 3 | 169.3 | 143.9 | 17.7 | 23.9 | NT* | NT | NT | NT |
| 4 | 162.5 | 124.9 | 18.2 | 17.4 | 403.7 | 49.6 | 25.5 | 14.5 |
| *NT = No test performed. | ||||||||
As can be seen from Table 2, the samples that were pre-solution treated at 1550° F. for 8 hours (i.e., Sample Group 2) had better tensile strength, yield strength, elongation, and reduction in area, significantly better stress-rupture life and impact strength than the samples that were not pre-solution treated (i.e. Sample Group 1), as well as those that were pre-solution treated at 1600° F. and 1650° F. for 8 hours (i.e. Sample Groups 3 and 4). Further, the properties of the Sample Group 4 samples were slightly lower than for the samples that were not pre-solution treated, but were still considered to be acceptable.
As previously discussed, pre-solution treating wrought nickel-base alloys at a temperature ranging from 1550° F. to 1600° F. can result in the advantageous precipitation of the at least one grain boundary phase. Further, as previously discussed, the grain boundary phase, when present in the desired amount and form, is believed to strengthen the grain boundaries of the nickel-base alloy and thereby cause an improvement in the elevated temperature properties of the alloys.
Test samples were prepared as discussed above in Example 1. The test samples were then divided into sample groups and the sample groups were subjected the solution and aging treatments indicated below in Table 3.
| TABLE 3 | |||
| Sample | First Aging | Second Aging | |
| Group | Solution Treatment | Treatment | Treatment |
| 5 | 1750° F. for 1 hour | 1325° F. for 8 hours | 1150° F. for 8 hours |
| 6 | 1750° F. for 1 hour | 1450° F. for 2 hours | 1200° F. for 8 hours |
| 7 | 1800° F. for 1 hour | 1325° F. for 8 hours | 1150° F. for 8 hours |
| 8 | 1800° F. for 1 hour | 1450° F. for 2 hours | 1200° F. for 8 hours |
Between solution treating and the first aging treatment, the samples were air cooled, while a cooling rate of about 100° F. per hour (i.e., furnace cooling) was employed between the first and second aging treatments. After the second aging treatment, the samples were cooled to room temperature by air cooling.
After heat treating, the samples from each group were tested as described above in Example 1, except that instead of the room temperature Charpy tests conducted above in Example 1, the samples of Sample Groups 5-8 were subjected to additional tensile testing at room temperature (“Trm”). The results of these tests are given below in Table 4, wherein the tabled values are average values for the samples tested.
| TABLE 4 | ||||||||||
| Stress- | % | |||||||||
| % | % | Rupture | EL at | |||||||
| UTS at | YS at | % | % | UTS at | YS at | EL at | RA at | Life at | Rupture | |
| Sample | Trm | Trm | EL at | RA at | 1300° F. | 1300° F. | 1300° | 1300° | 1300° F. | at |
| Group | (ksi) | (ksi) | Trm | Trm | (ksi) | (ksi) | F. | F. | (Hours) | 1300° F. |
| 5 | 205.9 | 158.9 | 25.5 | 38.2 | 164.1 | 135.1 | 16.3 | 17.8 | 386.2 | 36.4 |
| 6 | 218.8 | 174.7 | 21.9 | 35.7 | 170.3 | 145.7 | 19.3 | 18.1 | 433.1 | 35.4 |
| 7 | 205.1 | 155.6 | 27.4 | 44.8 | 147.6 | 114.7 | 14.4 | 21.0 | 330 | 49.0 |
| 8 | 205.3 | 149.9 | 27.8 | 44.0 | 160.7 | 125.2 | 12.4 | 14.1 | 1.9* | * |
| *Notch Break Observed | ||||||||||
As can be seen from the results in Table 4, the test samples of the Sample Groups 5, 6 and 8 had yield strengths of at least about 120 ksi at 1300° F., and percent elongations of at least about 12 percent at 1300° F. Further, Sample Groups 5-7 also had stress-rupture lives at 1300° F. and 80 ksi of at least about 300 hours and low notch sensitivity.
Between the two sample groups that were solution treated at 1750° F. (i.e., Sample Group 5 and Sample Group 6), the tensile and yield strength, both at room temperature and at 1300° F., the elevated temperature ductility, and the stress-rupture life of the Sample Group 6 test samples were generally improved as compared to the Sample Group 5 samples. Although not meant to be limiting herein, this is believed to be attributable to the higher aging temperatures used in aging the Sample Group 6 samples.
As further indicated in Table 4, notch breaks were observed in Sample Group 8. However, as indicated in Table 5, when stress-rupture testing was repeated on 4″ round forged billet samples that were heat treated in a manner similar to the Sample Group 8 samples, notch breaks were not observed. Although the repeat testing was performed on 4″ round forged billet samples as opposed to 8″ round forged billet samples, the absence of notch breaking is not believed to be attributable to the different size of the sample. Accordingly, heat treatments such as the one used to heat treat Sample Group 8 are believed to be suitable in developing nickel-base alloys having desirable stress-rupture properties.
| TABLE 5 | ||||
| Stress- | EL % at | |||
| Rupture Life | Rupture | |||
| Solution | First Aging | Second Aging | at 1300° F. | at |
| Treatment* | Treatment** | Treatment*** | and 80 ksi | 1300° F. |
| 1750° F. for | 1450° F. for | 1200° F. for | 558.4 | 27.6 |
| 1 Hour | 2 Hours | 8 Hours | ||
| 1800° F. for | 1450° F. for | 1200° F. for | 525.5 | 32.2 |
| 1 Hour | 2 Hours | 8 Hours | ||
| *Between solution treating and the first aging treatment, the samples were air cooled. | ||||
| **Between the first and second aging treatments, the samples were furnace cooled at a rate of about 100° F. per hour | ||||
| ***After the second aging treatment, the samples were cooled to room temperature by air cooling. | ||||
Test samples were prepared as discussed above in Example 1. The test samples were then divided into sample groups and the sample groups were then solution treated at 1750° F. for the times indicated below for each sample group in Table 6. After solution treatment, each of the test samples was air cooled to room temperature, and subsequently aged at 1450° F. for 2 hours, furnace cooled to 1200° F., and aged for 8 hours before being air cooled to room temperature.
| TABLE 6 | |||
| Sample Group | Solution Treatment Time | ||
| 9 | 1 | Hour | ||
| 10 | 3 | Hours | ||
| 11 | 4 | Hours | ||
After heat treating, the samples from each sample group were tested as described above in Example 1, except that Charpy impact testing was not conducted on the test samples. The results of these tests are given below in Table 7, wherein the tabled values are average values for the samples tested.
| TABLE 7 | ||||||
| Stress- | ||||||
| Tensile | Yield | Percent | Rupture | Percent | ||
| Strength | Strength | Percent | Reduction | Life at | Elongation | |
| Sample | at 1300° F. | at 1300° F. | Elongation | in Area at | 1300° F. | at Rupture |
| Group | (ksi) | (ksi) | at 1300° F. | 1300° F. | (Hours) | at 1300° F. |
| 9 | 170.3 | 145.7 | 19.3 | 18.1 | 433.1 | 35.4 |
| 10 | 162.5 | 132.6 | 27.8 | 33.8 | 190.4 | 32.8 |
| 11 | 162.6 | 136.7 | 25.8 | 30.6 | 185.1 | 47.5 |
As can be seen from the data in Table 7, while only Sample Group 9 had a stress-rupture life of at least 300 hours at 1300° F. and 80 ksi, all of the samples had yield strengths at 1300° F. of at least 120 ksi and percent elongations at 1300° F. of at least 12 percent. Although the stress-rupture properties of Sample Groups 10 and 11 are lower than those of Sample Group 9, it is believed that solution treatment times greater than 2 hours may, nevertheless, be useful in certain applications. Further, as previously discussed, when larger sized samples or work-pieces are heat treated, solution times greater than 2 hours may be required in order to dissolve substantially all of the γ′ and γ″-phase precipitates.
Test samples were prepared from a 4″ diameter, round-cornered, square reforged billet having a grain size ranging from ASTM 4.5 to ASTM 5.5, with an average grain size of ASTM 5, as determined according to ASTM E 112. The test samples were then divided into sample groups and the sample groups were solution treated at 1750° F. for 1 hour and cooled to room temperature at the cooling rates indicated below for each sample group in Table 8. After cooling to room temperature, the samples were aged at 1450° F. for 2 hours, furnace cooled to 1200° F., and aged for 8 hours before being air cooling to room temperature.
| TABLE 8 | |
| Sample Group | Cooling Rate After Solution Treatment |
| 12 | about 22,500° F./Hour (Air Cool) |
| 13 | 1000° F./Hour |
| 14 | 400° F./Hour |
After heat treating, the samples from each sample group were tested as described above in Example 3. The results of these tests are given below in Table 9, wherein the tabled values are average values for the samples tested.
| TABLE 9 | ||||||
| Stress- | ||||||
| Tensile | Yield | Percent | Rupture | Percent | ||
| Strength | Strength | Percent | Reduction | Life at | Elongation | |
| Sample | at 1300° F. | at 1300° F. | Elongation | in Area at | 1300° F. | at Rupture |
| Group | (ksi) | (ksi) | at 1300° F. | 1300° F. | (Hours) | at 1300° F. |
| 12 | 154.7 | 127.2 | 22.6 | 28.1 | 315.5 | 35.4 |
| 13 | 155.0 | 122.9 | 34.0 | 54.9 | 591.4 | 40.3 |
| 14 | 144.8 | 110.0 | 38.3 | 75.5 | 363.5 | 26.3 |
As can be seen from the data in Table 9, when the cooling rate after solution treatment was low (e.g., 400° F. per hour for Sample Group 14), yield strengths less than 120 ksi at 1300° F. were achieved. At higher cooling rates (e.g., 1000° F. per hour for Sample Group 13 and 22,500° F. per hour for sample group 14), yield strengths of at least 120 ksi at 1300° F. were observed. However, percent elongations at 1300° F. of at least 12 percent and stress-rupture lives of at least 300 hours at 1300° F. and 80 ksi were observed for all samples.
Test samples were prepared as discussed above in Example 1. Thereafter, the test samples were divided into Sample Groups 15-21. The samples were solution treated at 1750° F. for 1 hour. After solution treatment, the samples were cooled to room temperature at a rate of about 22,500° F. per hour (air cool) prior to aging as indicated in Table 10.
After the first aging treatment, all of the samples were furnace cooled to the second aging temperature, resulting in an average cooling rate of about 50° F. to about 100° F. per hour. Further, after the second aging treatment was completed, the samples were air cooled to room temperature.
| TABLE 10 | |||
| First Aging | Second Aging | ||
| Treatment | Treatment | ||
| Aging | Aging | |||
| Sample | Temperature | Aging Time | Temperature | Aging Time |
| Group # | (° F.) | (Hours) | (° F.) | (Hours) |
| 15 | 1365 | 8 | 1150 | 8 |
| 16 | 1365 | 8 | 1200 | 8 |
| 17 | 1400 | 8 | 1150 | 8 |
| 18 | 1400 | 8 | 1200 | 8 |
| 19 | 1450 | 8 | 1200 | 8 |
| 20 | 1450 | 2 | 1150 | 8 |
| 21 | 1450 | 2 | 1200 | 8 |
After heat treating, at least 2 samples from each sample group were tested as described above in Example 3. The results of these tests are given below in Table 11, wherein the tabled values are average values for the samples tested.
| TABLE 11 | ||||||
| Stress- | ||||||
| Tensile | Yield | Percent | Rupture | Percent | ||
| Strength | Strength | Percent | Reduction | Life at | Elongation | |
| Sample | at 1300° F. | at 1300° F. | Elongation | in Area at | 1300° F. | at Rupture |
| Group | (ksi) | (ksi) | at 1300° F. | 1300° F. | (Hours) | at 1300° F. |
| 15 | 165.4 | 138.8 | 19.1 | 20.6 | 342.5 | 30.6 |
| 16 | 165.6 | 135.5 | 18.9 | 24.5 | 349.0 | 37.5 |
| 17 | 169.5 | 141.0 | 16.3 | 21.8 | 311.5 | 36.5 |
| 18 | 162.2 | 123.6 | 16.6 | 19.8 | 313.7 | 47.0 |
| 19 | 165.2 | 141.2 | 30.5 | 48.7 | 312.5 | 34.5 |
| 20 | 165.7 | 135.2 | 16.9 | 18.6 | 361.3 | 32.7 |
| 21 | 170.3 | 145.7 | 19.3 | 18.1 | 433.1 | 35.4 |
The thermal stability of the mechanical properties at elevated temperatures of the test samples was also tested by exposing at least 2 samples from each sample group to 1400° F. for 100 hours prior to testing as indicated above. The results of these tests are given in Table 12 below.
| TABLE 12 | ||||||
| *Stress- | ||||||
| *Tensile | *Yield | *Percent | Rupture | *Percent | ||
| Strength | Strength | *Percent | Reduction | Life at | Elongation | |
| Sample | at 1300° F. | at 1300° F. | Elongation | in Area at | 1300° F. | at Rupture |
| Group | (ksi) | (ksi) | at 1300° F. | 1300° F. | (Hours) | at 1300° F. |
| 15 | 161.4 | 134.3 | 28.1 | 32.3 | 452.5 | 21.9 |
| 16 | 163.3 | 131.2 | 18.8 | 17.5 | 382.1 | 40.8 |
| 17 | 154.3 | 127.9 | 38.0 | 70.0 | 367.0 | 34.6 |
| 18 | 153.3 | 125.3 | 34.9 | 46.2 | 418.1 | 33.7 |
| 19 | 157.5 | 131.0 | 40.2 | 60.2 | 276.8 | 33.0 |
| 20 | 150.9 | 132.6 | 35.5 | 50.9 | 507.2 | 31.8 |
| 21 | 161.7 | 138.1 | 33.2 | 49.1 | 517.1 | 42.8 |
| *Exposed at 1400° F. for 100 hours prior to testing. | ||||||
As can be seen from the data of Tables 11 and 12, samples aged at a first aging temperature of about 1450° F. for 2 hours and a second aging temperature of about 1200° F. for 8 hours (i.e., Sample Group 21) had the highest combination of 1300° F. ultimate tensile and yield strengths and the highest stress-rupture life. After thermal exposure at 1400° F. (Table 12), the samples of Sample Group 21 had the highest 1300° F. yield strength and stress-rupture life. These results were followed closely by samples from Groups 15, 16, and 20.
Further, it can be seen that the ductility of the alloys was improved after long-term thermal exposure. Although not meant to be bound by any particular theory, it is believed that because the samples were not pre-solution treated and the cooling rate employed in cooling the samples from the solution temperature was high (about 22,500° F./hour), formation of desirable grain boundary δ/η-phase precipitates, as previously discussed in detail, was not achieved until after thermal exposure.
It is to be understood that the present description illustrates aspects of the invention relevant to a clear understanding of the invention. Certain aspects of the invention that would be apparent to those of ordinary skill in the art and that, therefore, would not facilitate a better understanding of the invention have not been presented in order to simplify the present description. Although the present invention has been described in connection with certain embodiments, the present invention is not limited to the particular embodiments disclosed, but is intended to cover modifications that are within the spirit and scope of the invention, as defined by the appended claims.
Claims (12)
1. A method of heat treating a 718-type nickel-base alloy, comprising:
selecting a 718-type nickel-base alloy;
solution treating the 718-type nickel-base alloy at a solution heat treat temperature greater than or equal to about 100° F. less than a γ′ and γ″ phase solvus temperature of the 718-type nickel alloy, and less than a δ and η phase solvus temperature of the 718-type nickel alloy, and for a solution heat treatment time sufficient to retain an amount of at least one grain boundary precipitate;
wherein the at least one grain boundary precipitate comprises a δ-phase precipitate, an η-phase precipitate, or mixtures thereof;
cooling the 718-type nickel-base alloy at a first cooling rate after solution treating the 718-type nickel-base alloy, wherein the first cooling rate is sufficient to substantially suppress precipitation and coarsening of a γ′-phase precipitate and a γ″-phase precipitate;
first step aging the solution treated 718-type nickel-base alloy for a first step aging time and a first step aging temperature;
wherein the first step aging temperature is below the γ′ and γ″ phase solvus temperature of the 718-type nickel alloy so that during the first step aging time an amount of primary γ′-phase grain matrix precipitates and an amount of primary γ″-phase grain matrix precipitates are formed; and
second step aging the 718-type nickel-base alloy for a second step aging time and a second step aging temperature to form a heat treated 718-type nickel-base alloy;
wherein the second step aging temperature is sufficiently less than the first step aging temperature so that an amount of secondary γ′-phase grain matrix precipitates and an amount of secondary γ″-phase grain matrix precipitates are formed during the second step aging time that are generally finer than the primary γ′-phase grain matrix precipitates and the primary γ″ phase grain matrix precipitates;
wherein the primary and secondary γ′-phase grain matrix precipitates and the primary and secondary γ″-phase grain matrix precipitates are the predominant strengthening precipitates in the heat treated 718-type nickel-base alloy;
wherein the amount of at least one grain boundary precipitate in the heat treated 718-type nickel-base alloy comprises short, generally rod-shaped morphologies and is sufficient to pin a majority of grain boundaries in place; and
wherein the heat treated 718-type nickel-base alloy comprises thermally stable mechanical properties.
2. The method of claim 1 , wherein selecting the 718-type nickel alloy comprises selecting an alloy that comprises in weight percent, up to 0.1% carbon, from 12% to 20% chromium, up to 4% molybdenum, up to 6% tungsten, from 5% to 12% cobalt, up to 14% iron, from 4% to 8% niobium, from 0.6% to 2.6% aluminum, from 0.4% to 1.4% titanium, from 0.003% to 0.03% phosphorus, from 0.003% to 0.015% boron, and balance nickel;
wherein a sum of the weight percent of molybdenum and the weight percent of tungsten is at least 2% and not more than 8%;
wherein a sum of atomic percent aluminum and atomic percent titanium is from 2%to 6%;
wherein a ratio of atomic percent aluminum to atomic percent titanium is at least 1.5; and
wherein the sum of atomic percent aluminum and atomic percent titanium, that sum divided by atomic percent niobium is from 0.8 to 1.3.
3. The method of claim 2 , wherein the solution heat treatment time is no greater than 4 hours.
4. The method of claim 2 , wherein the solution heat temperature is in a range from 1725° F. to 1850° F.
5. The method of claim 2 , wherein solution treating the 718-type nickel-base alloy comprises a solution treatment time no greater than 2 hours at a solution treatment temperature ranging from 1750° F. to 1800° F.
6. The method of claim 2 , wherein the first step aging time is no more than 8 hours.
7. The method of claim 2 , wherein the first step aging temperature is from about 1365° F. to about 1450° F.
8. The method of claim 2 , wherein the second step aging time is at least 8 hours.
9. The method of claim 2 wherein the second step aging temperature is from about 1150° F. to about 1300° F.
10. The method of claim 2 wherein the second aging treatment temperature is from about 1150° F. to about 1200° F.
11. The method of claim 2 wherein the heat treated 718-type nickel-base alloy has a yield strength at 1300° F. of at least 120 ksi, a percent elongation at 1300° F. of at least 12 percent, a notched stress-rupture life of at least 300 hours as measured at 1300° F. and 80 ksi, and a low notch-sensitivity.
12. The method of claim 1 , wherein the first cooling rate is at least 800° F. per hour.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/544,984 US7527702B2 (en) | 2003-10-06 | 2006-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/679,899 US7156932B2 (en) | 2003-10-06 | 2003-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
| US11/544,984 US7527702B2 (en) | 2003-10-06 | 2006-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
Related Parent Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US10/679,899 Division US7156932B2 (en) | 2003-10-06 | 2003-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
| US10/679,899 Continuation US7156932B2 (en) | 2003-10-06 | 2003-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| US20070029017A1 US20070029017A1 (en) | 2007-02-08 |
| US7527702B2 true US7527702B2 (en) | 2009-05-05 |
Family
ID=34394268
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US10/679,899 Active 2024-05-16 US7156932B2 (en) | 2003-10-06 | 2003-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
| US11/544,984 Expired - Lifetime US7527702B2 (en) | 2003-10-06 | 2006-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
| US11/544,808 Expired - Lifetime US7491275B2 (en) | 2003-10-06 | 2006-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US10/679,899 Active 2024-05-16 US7156932B2 (en) | 2003-10-06 | 2003-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US11/544,808 Expired - Lifetime US7491275B2 (en) | 2003-10-06 | 2006-10-06 | Nickel-base alloys and methods of heat treating nickel-base alloys |
Country Status (12)
| Country | Link |
|---|---|
| US (3) | US7156932B2 (en) |
| EP (3) | EP2770081B1 (en) |
| JP (1) | JP4995570B2 (en) |
| KR (1) | KR101193288B1 (en) |
| CN (1) | CN1890395B (en) |
| AU (1) | AU2004282496B2 (en) |
| BR (1) | BRPI0415106B1 (en) |
| CA (1) | CA2540212C (en) |
| DK (3) | DK2770080T3 (en) |
| MX (1) | MXPA06003569A (en) |
| RU (1) | RU2361009C2 (en) |
| WO (1) | WO2005038069A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110206553A1 (en) * | 2007-04-19 | 2011-08-25 | Ati Properties, Inc. | Nickel-base alloys and articles made therefrom |
| WO2013081770A1 (en) | 2011-11-30 | 2013-06-06 | Ati Properties, Inc. | Nickel-base alloy heat treatments, nickel-base alloys, and articles including nickel-base alloys |
| CN105051236A (en) * | 2013-02-22 | 2015-11-11 | 纳米钢公司 | Warm forming advanced high strength steel |
| US10287654B2 (en) | 2015-07-20 | 2019-05-14 | Rolls-Royce Plc | Ni-base alloy for structural applications |
| US10563293B2 (en) | 2015-12-07 | 2020-02-18 | Ati Properties Llc | Methods for processing nickel-base alloys |
Families Citing this family (60)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7156932B2 (en) * | 2003-10-06 | 2007-01-02 | Ati Properties, Inc. | Nickel-base alloys and methods of heat treating nickel-base alloys |
| US7531054B2 (en) * | 2005-08-24 | 2009-05-12 | Ati Properties, Inc. | Nickel alloy and method including direct aging |
| CN100424193C (en) * | 2006-02-09 | 2008-10-08 | 沈阳黎明航空发动机(集团)有限责任公司 | GH696 alloy vane ausform forming process |
| US8366652B2 (en) * | 2007-08-17 | 2013-02-05 | The Invention Science Fund I, Llc | Systems, devices, and methods including infection-fighting and monitoring shunts |
| CN101372730B (en) * | 2007-08-22 | 2011-01-26 | 中国科学院金属研究所 | Gamma strengthened high performance casting nickel-based high-temperature alloy |
| US20090057275A1 (en) * | 2007-08-31 | 2009-03-05 | General Electric Company | Method of Repairing Nickel-Based Alloy Articles |
| CN100590210C (en) * | 2007-09-19 | 2010-02-17 | 中国科学院金属研究所 | Technological process for improving twin boundary amount in gamma' precipitation strengthened type ferrous alloy |
| EP2205771B1 (en) | 2007-10-25 | 2019-04-03 | GKN Aerospace Sweden AB | Method, nickel base alloy and component |
| JP5299610B2 (en) * | 2008-06-12 | 2013-09-25 | 大同特殊鋼株式会社 | Method for producing Ni-Cr-Fe ternary alloy material |
| KR101007582B1 (en) * | 2008-06-16 | 2011-01-12 | 한국기계연구원 | Method of heat treatment of Ni based superalloy for wave type grain-boundary and Ni based superalloy the same |
| EP2145968A1 (en) * | 2008-07-14 | 2010-01-20 | Siemens Aktiengesellschaft | Nickel base gamma prime strengthened superalloy |
| US20100061875A1 (en) * | 2008-09-08 | 2010-03-11 | Siemens Power Generation, Inc. | Combustion Turbine Component Having Rare-Earth Elements and Associated Methods |
| DE102008047330B3 (en) * | 2008-09-16 | 2009-07-23 | Alstom Technology Ltd. | Process for the factory prefabrication of a heat-treated steel nickel alloy serpentine pipe in sections and subsequent on-site assembly |
| DE102008047329B3 (en) * | 2008-09-16 | 2009-07-23 | Alstom Technology Ltd. | Producing and mounting nickel alloy-based superheater tube coils, for steam generators, includes forming and hardening tubes in workshop before mounting and hardening weld seams on site |
| FR2941962B1 (en) * | 2009-02-06 | 2013-05-31 | Aubert & Duval Sa | PROCESS FOR MANUFACTURING A NICKEL-BASED SUPERALLIANCE WORKPIECE, AND A PRODUCT OBTAINED THEREBY |
| JP5104797B2 (en) * | 2009-03-31 | 2012-12-19 | 株式会社日立製作所 | Ni-base alloy heat treatment method and Ni-base alloy member regeneration method |
| JP5696995B2 (en) * | 2009-11-19 | 2015-04-08 | 独立行政法人物質・材料研究機構 | Heat resistant superalloy |
| US8608877B2 (en) | 2010-07-27 | 2013-12-17 | General Electric Company | Nickel alloy and articles |
| RU2455383C1 (en) * | 2011-05-05 | 2012-07-10 | Открытое акционерное общество "Всероссийский Институт Легких сплавов" (ОАО ВИЛС) | Method of heat treatment of details of heat-resistant nickel alloys for increasing resistance of low-cycle fatigue |
| JP5731915B2 (en) * | 2011-06-22 | 2015-06-10 | 川崎重工業株式会社 | Rotor for turbine, method for manufacturing the same, method and structure for joining Ni-base superalloy material and steel material |
| WO2013143995A1 (en) * | 2012-03-27 | 2013-10-03 | Alstom Technology Ltd | Method for manufacturing components made of single crystal (sx) or directionally solidified (ds) nickelbase superalloys |
| CN104364045B (en) * | 2012-05-11 | 2016-10-12 | 西门子能量股份有限公司 | The laser additive of nickel-based superalloy component is repaired |
| CN102912269B (en) * | 2012-10-24 | 2014-07-02 | 中国航空工业集团公司北京航空材料研究院 | Heat treatment method for recovering properties of aged solid-solution reinforced nickel-base high-temperature alloy |
| DE102013002483B4 (en) * | 2013-02-14 | 2019-02-21 | Vdm Metals International Gmbh | Nickel-cobalt alloy |
| EP2815841B1 (en) | 2013-06-18 | 2016-02-10 | Alstom Technology Ltd | Method for post-weld heat treatment of welded components made of gamma prime strengthened superalloys |
| TWI482862B (en) * | 2013-07-25 | 2015-05-01 | China Steel Corp | Austenitic alloy and method of making the same |
| US9828658B2 (en) | 2013-08-13 | 2017-11-28 | Rolls-Royce Corporation | Composite niobium-bearing superalloys |
| US9938610B2 (en) | 2013-09-20 | 2018-04-10 | Rolls-Royce Corporation | High temperature niobium-bearing superalloys |
| CN103643188B (en) * | 2013-10-29 | 2016-03-02 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of K465 alloy turbine blade restorability heat treating method |
| US9840752B2 (en) * | 2014-05-27 | 2017-12-12 | Keystone Engineering Company | Method and apparatus for performing a localized post-weld heat treatment on a thin wall metallic cylinder |
| JP5869624B2 (en) * | 2014-06-18 | 2016-02-24 | 三菱日立パワーシステムズ株式会社 | Ni-base alloy softening material and method for manufacturing Ni-base alloy member |
| EP3124641B1 (en) * | 2014-07-23 | 2021-05-05 | IHI Corporation | Method of manufacturing ni alloy part |
| CN104805259A (en) * | 2015-04-22 | 2015-07-29 | 绍兴文理学院 | Nickel base alloy composition matching and delta-phase spheroidizing heat treatment process |
| US10774407B2 (en) | 2015-06-19 | 2020-09-15 | University Of Florida Research Foundation, Inc. | Nickel titanium alloys, methods of manufacture thereof and article comprising the same |
| DE102015219351A1 (en) | 2015-10-07 | 2017-04-13 | Siemens Aktiengesellschaft | Process for producing products of steel or titanium with a precipitation hardening nickel base alloy and component |
| CN105734241A (en) * | 2016-03-18 | 2016-07-06 | 贵州航天精工制造有限公司 | Heat treatment method for improving high-temperature endurance property of GH2132 bolt |
| US10280498B2 (en) * | 2016-10-12 | 2019-05-07 | Crs Holdings, Inc. | High temperature, damage tolerant superalloy, an article of manufacture made from the alloy, and process for making the alloy |
| EP3323531A1 (en) * | 2016-11-18 | 2018-05-23 | Ansaldo Energia IP UK Limited | Method for manufacturing a mechanical component |
| CN111051548B (en) * | 2017-04-21 | 2022-06-03 | Crs控股有限责任公司 | Precipitation hardenable cobalt-nickel based superalloys and articles made therefrom |
| CN107641780A (en) * | 2017-10-11 | 2018-01-30 | 南通聚星铸锻有限公司 | A kind of Ni-based precipitation hardenable high temperature alloy Technology for Heating Processing |
| US20190247921A1 (en) * | 2018-02-12 | 2019-08-15 | Honeywell International Inc. | Methods for additively manufacturing turbine engine components via binder jet printing with nickel-chromium-tungsten-molybdenum alloys |
| GB2571280A (en) * | 2018-02-22 | 2019-08-28 | Rolls Royce Plc | Method of manufacture |
| CN108441704A (en) * | 2018-03-15 | 2018-08-24 | 江苏理工学院 | A kind of Refractoloy material and its preparation process |
| CN109136717A (en) * | 2018-11-07 | 2019-01-04 | 成都先进金属材料产业技术研究院有限公司 | Low expansion superalloy heat treatment method |
| US11053577B2 (en) * | 2018-12-13 | 2021-07-06 | Unison Industries, Llc | Nickel-cobalt material and method of forming |
| CN109576621B (en) * | 2019-01-18 | 2020-09-22 | 中国航发北京航空材料研究院 | Precise heat treatment method for nickel-based wrought superalloy workpiece |
| CN109957745B (en) * | 2019-03-27 | 2020-11-13 | 中国航发北京航空材料研究院 | Heat treatment method for optimizing NiTi-Al-based powder alloy precipitated phase |
| CN110592505B (en) * | 2019-09-12 | 2020-10-20 | 中国航发北京航空材料研究院 | Solution treatment method for accurately controlling structural properties of GH720Li alloy |
| CN111187999B (en) * | 2020-02-17 | 2020-12-08 | 河北工业大学 | Heat treatment method for enhancing fuel gas corrosion resistance of polycrystalline Ni-Cr-Al-based alloy |
| CN113308654B (en) * | 2020-02-27 | 2022-04-08 | 南京理工大学 | Nickel-based alloy with nano structure and gamma' phase composite structure and preparation method thereof |
| CN111235434B (en) * | 2020-03-02 | 2021-07-30 | 北京钢研高纳科技股份有限公司 | Preparation method of nickel-based deformed superalloy wheel disc forging used at high temperature |
| WO2022132928A1 (en) | 2020-12-15 | 2022-06-23 | Battelle Memorial Institute | NiCrMoNb AGE HARDENABLE ALLOY FOR CREEP-RESISTANT HIGH TEMPERATURE APPLICATIONS, AND METHODS OF MAKING |
| US11827955B2 (en) | 2020-12-15 | 2023-11-28 | Battelle Memorial Institute | NiCrMoNb age hardenable alloy for creep-resistant high temperature applications, and methods of making |
| CN112705700B (en) * | 2020-12-18 | 2022-02-08 | 山东大学 | Method for improving high-temperature strength of Inconel 718 laser deposition layer |
| KR102507347B1 (en) * | 2021-02-10 | 2023-03-07 | 창원대학교 산학협력단 | Method of heat treatment for improving strength and ductility of additive manufactured superalloy |
| US11313014B1 (en) | 2021-03-04 | 2022-04-26 | National Chung Shan Institute Of Science And Technology | Nickel-based superalloy and material thereof |
| CN113025848B (en) * | 2021-05-24 | 2021-08-17 | 北京钢研高纳科技股份有限公司 | Iron-nickel-based precipitation strengthening type high-temperature alloy and preparation method and application thereof |
| CN113604762B (en) * | 2021-07-14 | 2022-04-26 | 北京科技大学 | Vacuum solid solution and aging treatment process for improving high-temperature plasticity of GH4738 alloy ring piece |
| US11807930B1 (en) | 2022-11-02 | 2023-11-07 | University Of Science And Technology Beijing | Vacuum solution and aging treatment process for improving high-temperature plasticity of GH4738 rings |
| CN115572930B (en) * | 2022-11-09 | 2023-08-29 | 江苏美特林科特殊合金股份有限公司 | Heat treatment method for improving comprehensive performance of nickel-based casting alloy |
Citations (58)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3046108A (en) | 1958-11-13 | 1962-07-24 | Int Nickel Co | Age-hardenable nickel alloy |
| US3677830A (en) | 1970-02-26 | 1972-07-18 | United Aircraft Corp | Processing of the precipitation hardening nickel-base superalloys |
| US3705827A (en) * | 1971-05-12 | 1972-12-12 | Carpenter Technology Corp | Nickel-iron base alloys and heat treatment therefor |
| US3975219A (en) | 1975-09-02 | 1976-08-17 | United Technologies Corporation | Thermomechanical treatment for nickel base superalloys |
| US4083734A (en) | 1975-07-18 | 1978-04-11 | Special Metals Corporation | Nickel base alloy |
| US4144102A (en) | 1976-07-08 | 1979-03-13 | The International Nickel Company, Inc. | Production of low expansion superalloy products |
| US4219592A (en) | 1977-07-11 | 1980-08-26 | United Technologies Corporation | Two-way surfacing process by fusion welding |
| US4236943A (en) | 1978-06-22 | 1980-12-02 | The United States Of America As Represented By The United States Department Of Energy | Precipitation hardenable iron-nickel-chromium alloy having good swelling resistance and low neutron absorbence |
| US4371404A (en) | 1980-01-23 | 1983-02-01 | United Technologies Corporation | Single crystal nickel superalloy |
| US4608094A (en) | 1984-12-18 | 1986-08-26 | United Technologies Corporation | Method of producing turbine disks |
| US4614550A (en) | 1983-12-21 | 1986-09-30 | Societe Nationale D'etude Et De Construction De Meteurs D'aviation S.N.E.C.M.A. | Thermomechanical treatment process for superalloys |
| US4624716A (en) | 1982-12-13 | 1986-11-25 | Armco Inc. | Method of treating a nickel base alloy |
| US4652315A (en) | 1983-06-20 | 1987-03-24 | Sumitomo Metal Industries, Ltd. | Precipitation-hardening nickel-base alloy and method of producing same |
| US4750944A (en) | 1985-12-30 | 1988-06-14 | United Technologies Corporation | Laves free cast+hip nickel base superalloy |
| US4777017A (en) | 1983-11-18 | 1988-10-11 | Office National D'etudes Et De Recherches Aerospatiales (Onera) | Low density nickel based superalloy |
| US4788036A (en) | 1983-12-29 | 1988-11-29 | Inco Alloys International, Inc. | Corrosion resistant high-strength nickel-base alloy |
| US4793868A (en) | 1986-09-15 | 1988-12-27 | General Electric Company | Thermomechanical method of forming fatigue crack resistant nickel base superalloys and product formed |
| US4798632A (en) | 1986-01-20 | 1989-01-17 | Mitsubishi Jukogyo Kabushiki Kaisha | Ni-based alloy and method for preparing same |
| US4814023A (en) | 1987-05-21 | 1989-03-21 | General Electric Company | High strength superalloy for high temperature applications |
| US4837384A (en) | 1986-06-04 | 1989-06-06 | Office National D'etudes Et De Recherche Aerospatiales | Nickel-based monocrystalline superalloy, in particular for the blades of a turbomachine |
| US4888253A (en) | 1985-12-30 | 1989-12-19 | United Technologies Corporation | High strength cast+HIP nickel base superalloy |
| US4981644A (en) | 1983-07-29 | 1991-01-01 | General Electric Company | Nickel-base superalloy systems |
| US5006163A (en) | 1985-03-13 | 1991-04-09 | Inco Alloys International, Inc. | Turbine blade superalloy II |
| US5047091A (en) | 1981-04-03 | 1991-09-10 | Office National D'etudes Et De Recherche Aerospatiales | Nickel based monocrystalline superalloy, method of heat treating said alloy, and parts made therefrom |
| US5077004A (en) | 1986-05-07 | 1991-12-31 | Allied-Signal Inc. | Single crystal nickel-base superalloy for turbine components |
| US5087305A (en) | 1988-07-05 | 1992-02-11 | General Electric Company | Fatigue crack resistant nickel base superalloy |
| US5104614A (en) | 1986-02-06 | 1992-04-14 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Superalloy compositions with a nickel base |
| US5129970A (en) | 1988-09-26 | 1992-07-14 | General Electric Company | Method of forming fatigue crack resistant nickel base superalloys and product formed |
| US5131961A (en) | 1988-09-30 | 1992-07-21 | Hitachi Metals, Ltd. | Method for producing a nickel-base superalloy |
| US5154884A (en) | 1981-10-02 | 1992-10-13 | General Electric Company | Single crystal nickel-base superalloy article and method for making |
| US5156808A (en) | 1988-09-26 | 1992-10-20 | General Electric Company | Fatigue crack-resistant nickel base superalloy composition |
| US5244515A (en) | 1992-03-03 | 1993-09-14 | The Babcock & Wilcox Company | Heat treatment of Alloy 718 for improved stress corrosion cracking resistance |
| US5328659A (en) | 1982-10-15 | 1994-07-12 | United Technologies Corporation | Superalloy heat treatment for promoting crack growth resistance |
| US5403546A (en) | 1989-02-10 | 1995-04-04 | Office National D'etudes Et De Recherches/Aerospatiales | Nickel-based superalloy for industrial turbine blades |
| US5424029A (en) | 1982-04-05 | 1995-06-13 | Teledyne Industries, Inc. | Corrosion resistant nickel base alloy |
| US5431750A (en) | 1991-06-27 | 1995-07-11 | Mitsubishi Materials Corporation | Nickel-base heat-resistant alloys |
| US5435861A (en) | 1992-02-05 | 1995-07-25 | Office National D'etudes Et De Recherches Aerospatiales | Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production |
| US5556594A (en) | 1986-05-30 | 1996-09-17 | Crs Holdings, Inc. | Corrosion resistant age hardenable nickel-base alloy |
| RU2088684C1 (en) | 1990-11-19 | 1997-08-27 | Инко Эллойз Интернэшнл Инк. | Oxidation-resistant alloy (variants) |
| RU2112069C1 (en) | 1996-06-14 | 1998-05-27 | Акционерное общество открытого типа "Пермские моторы" | Nickel-base cast high-temperature alloy |
| US5863494A (en) | 1995-11-17 | 1999-01-26 | Asea Brown Boveri Ag | Iron-nickel superalloy of the type in 706 |
| US5888316A (en) | 1992-08-31 | 1999-03-30 | Sps Technologies, Inc. | Nickel-cobalt based alloys |
| US5888315A (en) | 1995-03-07 | 1999-03-30 | Henkel Corporation | Composition and process for forming an underpaint coating on metals |
| US5916382A (en) | 1992-03-09 | 1999-06-29 | Hitachi, Ltd. | High corrosion resistant high strength superalloy and gas turbine utilizing the alloy |
| US6106767A (en) | 1995-12-21 | 2000-08-22 | Teledyne Industries, Inc. | Stress rupture properties of nickel-chromium-cobalt alloys by adjustment of the levels of phosphorus and boron |
| US6193823B1 (en) | 1999-03-17 | 2001-02-27 | Wyman Gordon Company | Delta-phase grain refinement of nickel-iron-base alloy ingots |
| US20010026769A1 (en) | 1997-10-31 | 2001-10-04 | Toshiharu Kobayashi | Nickel-based single crystal alloy and a method of manufacturing the same |
| US6315846B1 (en) | 1998-07-09 | 2001-11-13 | Inco Alloys International, Inc. | Heat treatment for nickel-base alloys |
| US6328827B1 (en) | 1994-07-13 | 2001-12-11 | Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA” | Method of manufacturing sheets made of alloy 718 for the superplastic forming of parts therefrom |
| US20020036037A1 (en) | 1994-06-24 | 2002-03-28 | Kennedy Richard L. | Nickel-based alloy having high stress rupture life |
| US6416564B1 (en) | 2001-03-08 | 2002-07-09 | Ati Properties, Inc. | Method for producing large diameter ingots of nickel base alloys |
| US6496529B1 (en) | 2000-11-15 | 2002-12-17 | Ati Properties, Inc. | Refining and casting apparatus and method |
| US20030034098A1 (en) | 2001-04-24 | 2003-02-20 | General Electric Company | Nickel-base superalloys and articles formed therefrom |
| US20030051777A1 (en) | 2001-09-18 | 2003-03-20 | Koji Sudo | Ni based alloy, method for producing the same, and forging die |
| US20030116242A1 (en) | 2001-12-20 | 2003-06-26 | Harrison William Henry | Method of restoration of mechanical properties of cast inconel 718 for serviced aircraft components |
| WO2003097888A1 (en) | 2002-05-13 | 2003-11-27 | Ati Properties, Inc. | Nickel-base alloy |
| US20050072500A1 (en) | 2003-10-06 | 2005-04-07 | Wei-Di Cao | Nickel-base alloys and methods of heat treating nickel-base alloys |
| US20070044875A1 (en) | 2005-08-24 | 2007-03-01 | Ati Properties, Inc. | Nickel alloy and method of direct aging heat treatment |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2677830A (en) * | 1950-03-09 | 1954-05-11 | Clyde H Allen | Ventilating means for toilet bowls |
| US3315846A (en) * | 1965-06-24 | 1967-04-25 | Landis H Richard | Liquid cooling and dispensing device |
| US4685978A (en) * | 1982-08-20 | 1987-08-11 | Huntington Alloys Inc. | Heat treatments of controlled expansion alloy |
| FR2615869A1 (en) * | 1987-05-27 | 1988-12-02 | Gen Electric | MOLDABLE AND WELDABLE SUPERALLOY, MOLDED CONSTRUCTION PARTS MADE OF SUCH ALLOY AND METHOD OF HEAT TREATING SUCH A PART |
| JP3084764B2 (en) * | 1991-03-08 | 2000-09-04 | 大同特殊鋼株式会社 | Method for manufacturing Ni-based superalloy member |
| CN1026710C (en) * | 1993-08-21 | 1994-11-23 | 冶金工业部钢铁研究总院 | Wear- and corrosion-resistant Ni-base alloy |
| FR2712307B1 (en) * | 1993-11-10 | 1996-09-27 | United Technologies Corp | Articles made of super-alloy with high mechanical and cracking resistance and their manufacturing process. |
| US5416564A (en) * | 1994-02-04 | 1995-05-16 | Xerox Corporatin | Xerographic process control using developer to photoreceptor current sensing for grid voltage adjust |
| JPH09268337A (en) * | 1996-04-03 | 1997-10-14 | Hitachi Metals Ltd | Forged high corrosion resistant superalloy alloy |
| EP1154027B1 (en) * | 1999-01-28 | 2004-11-10 | Sumitomo Electric Industries, Ltd. | Heat-resistant alloy wire |
| US6740177B2 (en) * | 2002-07-30 | 2004-05-25 | General Electric Company | Nickel-base alloy |
-
2003
- 2003-10-06 US US10/679,899 patent/US7156932B2/en active Active
-
2004
- 2004-09-28 CN CN2004800356839A patent/CN1890395B/en active Active
- 2004-09-28 EP EP14168520.6A patent/EP2770081B1/en active Active
- 2004-09-28 EP EP04785174.6A patent/EP1680525B1/en active Active
- 2004-09-28 MX MXPA06003569A patent/MXPA06003569A/en active IP Right Grant
- 2004-09-28 JP JP2006534008A patent/JP4995570B2/en active Active
- 2004-09-28 EP EP14168514.9A patent/EP2770080B1/en active Active
- 2004-09-28 DK DK14168514.9T patent/DK2770080T3/en active
- 2004-09-28 AU AU2004282496A patent/AU2004282496B2/en active Active
- 2004-09-28 KR KR1020067006510A patent/KR101193288B1/en active IP Right Grant
- 2004-09-28 DK DK14168520.6T patent/DK2770081T3/en active
- 2004-09-28 WO PCT/US2004/031760 patent/WO2005038069A1/en active Search and Examination
- 2004-09-28 RU RU2006115566/02A patent/RU2361009C2/en active
- 2004-09-28 DK DK04785174.6T patent/DK1680525T3/en active
- 2004-09-28 BR BRPI0415106-2B1A patent/BRPI0415106B1/en active IP Right Grant
- 2004-09-28 CA CA2540212A patent/CA2540212C/en active Active
-
2006
- 2006-10-06 US US11/544,984 patent/US7527702B2/en not_active Expired - Lifetime
- 2006-10-06 US US11/544,808 patent/US7491275B2/en not_active Expired - Lifetime
Patent Citations (61)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3046108A (en) | 1958-11-13 | 1962-07-24 | Int Nickel Co | Age-hardenable nickel alloy |
| US3677830A (en) | 1970-02-26 | 1972-07-18 | United Aircraft Corp | Processing of the precipitation hardening nickel-base superalloys |
| US3705827A (en) * | 1971-05-12 | 1972-12-12 | Carpenter Technology Corp | Nickel-iron base alloys and heat treatment therefor |
| US4083734A (en) | 1975-07-18 | 1978-04-11 | Special Metals Corporation | Nickel base alloy |
| US3975219A (en) | 1975-09-02 | 1976-08-17 | United Technologies Corporation | Thermomechanical treatment for nickel base superalloys |
| US4144102A (en) | 1976-07-08 | 1979-03-13 | The International Nickel Company, Inc. | Production of low expansion superalloy products |
| US4219592A (en) | 1977-07-11 | 1980-08-26 | United Technologies Corporation | Two-way surfacing process by fusion welding |
| US4236943A (en) | 1978-06-22 | 1980-12-02 | The United States Of America As Represented By The United States Department Of Energy | Precipitation hardenable iron-nickel-chromium alloy having good swelling resistance and low neutron absorbence |
| US4371404A (en) | 1980-01-23 | 1983-02-01 | United Technologies Corporation | Single crystal nickel superalloy |
| US5047091A (en) | 1981-04-03 | 1991-09-10 | Office National D'etudes Et De Recherche Aerospatiales | Nickel based monocrystalline superalloy, method of heat treating said alloy, and parts made therefrom |
| US5154884A (en) | 1981-10-02 | 1992-10-13 | General Electric Company | Single crystal nickel-base superalloy article and method for making |
| US5424029A (en) | 1982-04-05 | 1995-06-13 | Teledyne Industries, Inc. | Corrosion resistant nickel base alloy |
| US5328659A (en) | 1982-10-15 | 1994-07-12 | United Technologies Corporation | Superalloy heat treatment for promoting crack growth resistance |
| US4624716A (en) | 1982-12-13 | 1986-11-25 | Armco Inc. | Method of treating a nickel base alloy |
| US4652315A (en) | 1983-06-20 | 1987-03-24 | Sumitomo Metal Industries, Ltd. | Precipitation-hardening nickel-base alloy and method of producing same |
| US4981644A (en) | 1983-07-29 | 1991-01-01 | General Electric Company | Nickel-base superalloy systems |
| US4777017A (en) | 1983-11-18 | 1988-10-11 | Office National D'etudes Et De Recherches Aerospatiales (Onera) | Low density nickel based superalloy |
| US4614550A (en) | 1983-12-21 | 1986-09-30 | Societe Nationale D'etude Et De Construction De Meteurs D'aviation S.N.E.C.M.A. | Thermomechanical treatment process for superalloys |
| US4788036A (en) | 1983-12-29 | 1988-11-29 | Inco Alloys International, Inc. | Corrosion resistant high-strength nickel-base alloy |
| US4608094A (en) | 1984-12-18 | 1986-08-26 | United Technologies Corporation | Method of producing turbine disks |
| US5006163A (en) | 1985-03-13 | 1991-04-09 | Inco Alloys International, Inc. | Turbine blade superalloy II |
| US4888253A (en) | 1985-12-30 | 1989-12-19 | United Technologies Corporation | High strength cast+HIP nickel base superalloy |
| US4750944A (en) | 1985-12-30 | 1988-06-14 | United Technologies Corporation | Laves free cast+hip nickel base superalloy |
| US4798632A (en) | 1986-01-20 | 1989-01-17 | Mitsubishi Jukogyo Kabushiki Kaisha | Ni-based alloy and method for preparing same |
| US5104614A (en) | 1986-02-06 | 1992-04-14 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Superalloy compositions with a nickel base |
| US5077004A (en) | 1986-05-07 | 1991-12-31 | Allied-Signal Inc. | Single crystal nickel-base superalloy for turbine components |
| US5556594A (en) | 1986-05-30 | 1996-09-17 | Crs Holdings, Inc. | Corrosion resistant age hardenable nickel-base alloy |
| US4837384A (en) | 1986-06-04 | 1989-06-06 | Office National D'etudes Et De Recherche Aerospatiales | Nickel-based monocrystalline superalloy, in particular for the blades of a turbomachine |
| US4793868A (en) | 1986-09-15 | 1988-12-27 | General Electric Company | Thermomechanical method of forming fatigue crack resistant nickel base superalloys and product formed |
| US4814023A (en) | 1987-05-21 | 1989-03-21 | General Electric Company | High strength superalloy for high temperature applications |
| US5087305A (en) | 1988-07-05 | 1992-02-11 | General Electric Company | Fatigue crack resistant nickel base superalloy |
| US5156808A (en) | 1988-09-26 | 1992-10-20 | General Electric Company | Fatigue crack-resistant nickel base superalloy composition |
| US5129970A (en) | 1988-09-26 | 1992-07-14 | General Electric Company | Method of forming fatigue crack resistant nickel base superalloys and product formed |
| US5131961A (en) | 1988-09-30 | 1992-07-21 | Hitachi Metals, Ltd. | Method for producing a nickel-base superalloy |
| US5403546A (en) | 1989-02-10 | 1995-04-04 | Office National D'etudes Et De Recherches/Aerospatiales | Nickel-based superalloy for industrial turbine blades |
| RU2088684C1 (en) | 1990-11-19 | 1997-08-27 | Инко Эллойз Интернэшнл Инк. | Oxidation-resistant alloy (variants) |
| US5431750A (en) | 1991-06-27 | 1995-07-11 | Mitsubishi Materials Corporation | Nickel-base heat-resistant alloys |
| US5435861A (en) | 1992-02-05 | 1995-07-25 | Office National D'etudes Et De Recherches Aerospatiales | Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production |
| US5244515A (en) | 1992-03-03 | 1993-09-14 | The Babcock & Wilcox Company | Heat treatment of Alloy 718 for improved stress corrosion cracking resistance |
| US5916382A (en) | 1992-03-09 | 1999-06-29 | Hitachi, Ltd. | High corrosion resistant high strength superalloy and gas turbine utilizing the alloy |
| US5888316A (en) | 1992-08-31 | 1999-03-30 | Sps Technologies, Inc. | Nickel-cobalt based alloys |
| US20020036037A1 (en) | 1994-06-24 | 2002-03-28 | Kennedy Richard L. | Nickel-based alloy having high stress rupture life |
| US6328827B1 (en) | 1994-07-13 | 2001-12-11 | Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “SNECMA” | Method of manufacturing sheets made of alloy 718 for the superplastic forming of parts therefrom |
| US5888315A (en) | 1995-03-07 | 1999-03-30 | Henkel Corporation | Composition and process for forming an underpaint coating on metals |
| US5863494A (en) | 1995-11-17 | 1999-01-26 | Asea Brown Boveri Ag | Iron-nickel superalloy of the type in 706 |
| US6106767A (en) | 1995-12-21 | 2000-08-22 | Teledyne Industries, Inc. | Stress rupture properties of nickel-chromium-cobalt alloys by adjustment of the levels of phosphorus and boron |
| RU2112069C1 (en) | 1996-06-14 | 1998-05-27 | Акционерное общество открытого типа "Пермские моторы" | Nickel-base cast high-temperature alloy |
| US20010026769A1 (en) | 1997-10-31 | 2001-10-04 | Toshiharu Kobayashi | Nickel-based single crystal alloy and a method of manufacturing the same |
| US6315846B1 (en) | 1998-07-09 | 2001-11-13 | Inco Alloys International, Inc. | Heat treatment for nickel-base alloys |
| US6193823B1 (en) | 1999-03-17 | 2001-02-27 | Wyman Gordon Company | Delta-phase grain refinement of nickel-iron-base alloy ingots |
| US6496529B1 (en) | 2000-11-15 | 2002-12-17 | Ati Properties, Inc. | Refining and casting apparatus and method |
| US6719858B2 (en) | 2001-03-08 | 2004-04-13 | Ati Properties, Inc. | Large diameter ingots of nickel base alloys |
| US6416564B1 (en) | 2001-03-08 | 2002-07-09 | Ati Properties, Inc. | Method for producing large diameter ingots of nickel base alloys |
| US20030034098A1 (en) | 2001-04-24 | 2003-02-20 | General Electric Company | Nickel-base superalloys and articles formed therefrom |
| US20030051777A1 (en) | 2001-09-18 | 2003-03-20 | Koji Sudo | Ni based alloy, method for producing the same, and forging die |
| US20030116242A1 (en) | 2001-12-20 | 2003-06-26 | Harrison William Henry | Method of restoration of mechanical properties of cast inconel 718 for serviced aircraft components |
| WO2003097888A1 (en) | 2002-05-13 | 2003-11-27 | Ati Properties, Inc. | Nickel-base alloy |
| US20050072500A1 (en) | 2003-10-06 | 2005-04-07 | Wei-Di Cao | Nickel-base alloys and methods of heat treating nickel-base alloys |
| WO2005038069A1 (en) | 2003-10-06 | 2005-04-28 | Ati Properties, Inc. | Nickel-base alloys and methods of heat treating nickel-base alloys |
| US20070029014A1 (en) | 2003-10-06 | 2007-02-08 | Ati Properties, Inc. | Nickel-base alloys and methods of heat treating nickel-base alloys |
| US20070044875A1 (en) | 2005-08-24 | 2007-03-01 | Ati Properties, Inc. | Nickel alloy and method of direct aging heat treatment |
Non-Patent Citations (48)
| Title |
|---|
| "Technical Data Sheet Allvac(R) 718 Alloy" Allvac, Monroe, NC (2000). |
| Allvac(R) 718 Alloy Technical Data Sheet dated Dec. 31, 2001, 2 pages. |
| Allvac(R) 718 Plus(TM) Alloy Technical Data Sheet dated May 6, 2005, 3 pages. |
| Allvac(R) 718Plus(R) Alloy Technical Data Sheet dated Aug. 3, 2005, 3 pages. |
| Andrieu, E. et al. "Influence of Compositional Modifications on Thermal Stability of Alloy 718," Superalloys 718, 625, 706 and Various Derivatives, E. A. Loria ed., The Minerals, Metals & Materials Society, Warrendale, PA (1994), pp. 695-710. |
| Andrieu, E. et al., "Effect of Environment and Microstructure on the High Temperature Behaviour of Alloy 718," Superalloy 718- Metallurgy and Applications, E. A. Loria ed., The Minerals, Metals & Materials Society, Warrendale, PA (1989), pp. 241-256. |
| ASM Handbook, vol. 14, fourth printing, (1996), electronic file, pp. 1-18. |
| Azadian, S. et al. "Precipitation in Spray-Formed IN718," Proceedings of the 5th International Symposium on Superalloys 718, 625, 706 and Various Derivatives, E. A. Loria ed., The Minerals, Metals & Materials Society, Warrendale, PA (2001), pp. 617-626. |
| Barker et al., "Thermomechanical Processing of Inconel 718 and Its Effect on Properties," Advanced High Temperature Alloy: Processing and Properties, ASM, 1986, pp. 125-137. |
| Bond et al., "Evaluation of Allvac(R) 718PLUS(TM) Alloy in the Cold Worked and Heat Treated Condition," Superalloys 718, 625, 706 and Derivatives 2005, ed. E.A. Loria, The Minerals, Metals & Materials Society, 2005, pp. 203-211. |
| Burke et al., "Microstructure and Properties of Direct-Aged Alloy 625," Superalloys 718, 625, 706 and Various Derivatives, E.A. Loria Ed., The Minerals, Metals and Materials Society, 2001 pp. 389-398. |
| Cao et al., "Effect and Mechanism of Phosphorous and Boron on Creep Deformation of Alloy 718," Superalloys 718, 625, 706 and Various Derivatives, ed. E.A. Loria, 1997, pp. 511-520. |
| Cao et al., "Phosphorous-Boron Interaction in Nickel-Base Superalloys," Superalloys 1996, The Minerals, Matels & Materials Society, pp. 589-597 (1996). |
| Cao et al., "Production Evaluation on 718-ER(R) Alloy," Superalloys 2000, The Mineral, Metals & Materials Society, pp. 101-108 (2000). |
| Cao et al., "The Effect of Phosphorous on Mechanical Properties of Alloy 718," Superalloys 718, 625, 706 and Various Derivatives, pp. 463-477 (1994). |
| Cao, U.S. Appl. No. 10/144,369, entitled "Nickel-Base Alloy," filed May 13, 2002 and assigned to ATI Properties, Inc. |
| Chang et al., "Rene 220: 100° F Improvement Over Alloy 718," Superalloy 718-Metallurgy and Applications, The Minerals, Metals & Materials Society, pp. 631-645 (1989). |
| Chen et al. "Strain-induced gamma'' phase precipitation and gamma'' -> delta transformation in inconel 718 alloy," Metal Journal, Feb. 2000, vol. 36(2), pp. 150-154. |
| Choudhury, Alok, "State of the Art Superalloy Production for Aerospace and Other Application Using VIM/VAR or VIM/ESR," from ISIJ International, vol. 32, No. 5, 1992. pp. 563-574. |
| Collier, John P. et al. "On Developing a Microstructurally and Thermally Stable Iron-Nickel Superalloy," S. Reichman et al. eds., The Metallurgical Society (1988), pp. 43-53 (1988). |
| Collier, John P. et al., "The Effect of Varying Al, Ti, and Nb Content on the Phase Stability of Inconel 718," Metallurgical Transactions A, vol. 19A, Jul. 1988, pp. 1657-1666. |
| Cordy et al., "Chemistry and Structure Control in Remelted Superalloy Ingots," Proceedings of the 1984 Vacuum Metallurgy Conference on Specialty Metals Melting and Processing, Pittsburgh, Pennsylvania, Jun. 11-13, 1984, pp. 69-74. |
| Du et al., "Microstructure and Mechanical Properties of Novel 718 Superalloy," Acta Metallurgical Sinica (English Letters), vol. 19, No. 6, Dec. 2006, pp. 418-424. |
| Gou, Encai et al., "Improving Thermal Stability of Alloy 718 Via Small Modifications in Composition," Superalloy 718- Metallurgy and Applications, E. A. Loria ed., The Minerals, Metals & Materials Society, Warrendale, PA (1989), pp. 567-576. |
| Guo, Encai et al., "Further Studies on Thermal Stability of Modified 718 Alloys," Superalloys 718, 625, 706 and Various Derivatives, E. A. Loria ed., The Minerals, Metals & Materials Society, Warrendale, PA (1994), pp. 721-734. |
| Himushin, F.F., High Temperature Strength Metals and Alloys,: Moscow, 'Metallurgy' Publisher, 1969, pp. 443-449, 471. |
| Horvath et al., "The Effectiveness of Direct Aging on Inconel 718 Forgings Produced at High Strain Rates as Obtained on a Screw Press," Superalloys 718, 625, 706 and Various Derivatives, E.A. Loria Ed., The Mineral, Metals & Materials Society, 2001, pp. 223-228. |
| Kennedy et al. "Developments in Wrought Nb Containing Superalloys (718 + 100 F)," Proceedings of the International Symposium on Niobium for High Temperature Application, Araxa, Brazil, Dec. 1-3, 2003, Published by TMS, indexed by Chemical Abstracts Service, Oct. 25, 2004, 12 pages. |
| Kennedy et al., "Large Diameter Superalloy Ingots," Advanced Technologies for Superalloy Affordability, ed. Chang et al., The Minerals, Metals & Materials Society, 2000, pp. 159-171. |
| Kennedy et al., "Stress-rupture Strength of Alloy 718," Advanced Materials & Processes, vol. 149, No. 3, Mar. 1996, pp. 33-35. |
| Kennedy, R. L., "Allvac(R) 718PLUS(TM), Superalloy for the Next Forty Years," Superalloys 718, 625, 706 and Derivatives 2005, ed. E.A. Loria, The Minerals, Metals & Materials Society, 2005, pp. 1-14. |
| Key to Metals Nonferrous, "Heat Treating of Nickel and Nickel Alloys," printed from http://www.key-to-nonferrous.com/default.aspx?ID=CheckArticle&NM=32 on Mar. 10, 2008, 1 pages. |
| Kissinger, Trends and Near Term Requirements of GE Aircraft Engines Titanium and Nickel Base Disk Alloys. From the Conference: Electron Beam Melting and Refining-State of the Art 1991 in Reno, Nevada. Oct. 1992, pp. 31-40. |
| Krueger, "The Development of Direct Age 718 for Gas Turbine Engine Disk Applications," Superalloy 718-Metallurgy and Applications, E.A. Loria Ed., The Minerals, Metals & Materials Society, 1989, pp. 279-296. |
| Mannan et al., "Physical Metallurgy of Alloys 718, 725, 725HS, 925 for Service in Aggressive Corrosive Environments," Special Metals Corporation, Huntington, West Virginia, undated, 12 pages. |
| Manriquez, J.A. et al. "The High Temperature Stability of IN718 Derivative Alloys" Superalloys (1992) pp. 507-516. |
| Metals Handbook(R), Tenth edition, vol. 1, Properties and Selection: Irons, Steels, and High-Performance Alloys, ASM International, 1990, p. 982. |
| Moyer et al. "Advances in Triple Melting Superalloys 718, 706 and 720," Proceedings of the International Symposium on Superalloys 718, 625, 706, and Various Derivatives Sponsored by the The Minerals, Metals & Materials Society, 1994. pp. 39-48. |
| R. Cozar et al., "Morphology of Y' and Y'' Precipitates and Thermal Stability of Inconel 718 Type Alloys," Metallurgical Transactions, vol. 4, Jan. 1973, pp. 47-59. |
| R. Warren, Liu-Ying Wei, Johan Ockborn "Interrelationships Between Thermomechancial Treatment, Microstructure and Properties of Nickel Base Superalloys," at http://www.ts.mah.se/forskn/mumat/Research/research-topic-rw.htm. (last updated Feb. 19, 2002). |
| Radavich et al. "Effects of Processing and Thermal Treatments on Alloy 720," Proceedings of the Tenth International Conference on Vacuum Metallurgy, vol. I, Beijing, P.R. China, 1990, pp. 42-53. |
| Schafrik et al., "Application of Alloy 718 in GE Aircraft Engines: Past, Present and the Next Five Years," Superalloys 718, 625, 706 and Various Derivatives, pp. 1-11 (2001). |
| Schwant, et al. "Large 718 Forgings for Land Based Turbines," Superalloys 718, 625, 706 and Various Derivatives, ed. E.A. Loria, The Minerals, Metals & Materials Society, Warrendale, PA, 1997, pp. 141-152. |
| Warren et al., "The Cyclic Fatigue Behavior of Direct Age 718 and 149, 315, 454 and 538 <?img id="CUSTOM-CHARACTER-00001" he="3.13mm" wi="1.02mm" file="US07527702-20090505-P00001.TIF" alt="custom character" img-content="character" img-format="tif" ?>C," Materials Science & Engineering, A vol. 428, 2006, pp. 106-115. |
| Xie et al., "Segregation Behavior of Phosphorous and Its Effect on Microstructure and Mechanical Properties in Alloy System Ni-Cr-Fe-Mo-Nb-Ti-Al," Superalloys 718, 625, 706 and Various Derivatives, ed. E.A. Loria, 1997, pp. 531-542. |
| Xie et al., "The Role of Phosphorous and Sulfur in Inconel 718," Superalloys 1996, The Minerals, Metals and Materials Society, pp. 599-606 (1996). |
| Xie, Xishan et al. "The Role of Mg on Structure and Mechanical Properties in Alloy 718," Superalloys 1988, S. Reichman et al. eds., The Metallurgical Society (1988), pp. 635-642. |
| Xie, Xishan et al., "The Role of Phosphorus and Sulfur in Inconel 718," Superalloys 1996, R.D. Kissinger et al. eds., The Minerals, Metals & Materials Society, Warrendale, PA (1996), pp. 599-606. |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110206553A1 (en) * | 2007-04-19 | 2011-08-25 | Ati Properties, Inc. | Nickel-base alloys and articles made therefrom |
| US8394210B2 (en) | 2007-04-19 | 2013-03-12 | Ati Properties, Inc. | Nickel-base alloys and articles made therefrom |
| WO2013081770A1 (en) | 2011-11-30 | 2013-06-06 | Ati Properties, Inc. | Nickel-base alloy heat treatments, nickel-base alloys, and articles including nickel-base alloys |
| CN105051236A (en) * | 2013-02-22 | 2015-11-11 | 纳米钢公司 | Warm forming advanced high strength steel |
| US10287654B2 (en) | 2015-07-20 | 2019-05-14 | Rolls-Royce Plc | Ni-base alloy for structural applications |
| US10563293B2 (en) | 2015-12-07 | 2020-02-18 | Ati Properties Llc | Methods for processing nickel-base alloys |
| US11725267B2 (en) | 2015-12-07 | 2023-08-15 | Ati Properties Llc | Methods for processing nickel-base alloys |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1890395B (en) | 2010-06-16 |
| DK2770080T3 (en) | 2017-02-20 |
| EP2770080B1 (en) | 2016-12-14 |
| EP2770081A2 (en) | 2014-08-27 |
| EP1680525B1 (en) | 2014-07-02 |
| CA2540212C (en) | 2011-11-15 |
| BRPI0415106A (en) | 2006-11-28 |
| US20070029017A1 (en) | 2007-02-08 |
| JP2007510055A (en) | 2007-04-19 |
| EP2770080A3 (en) | 2014-11-05 |
| WO2005038069A1 (en) | 2005-04-28 |
| EP2770081B1 (en) | 2016-12-14 |
| KR101193288B1 (en) | 2012-11-02 |
| US7491275B2 (en) | 2009-02-17 |
| DK2770081T3 (en) | 2017-02-20 |
| KR20060119997A (en) | 2006-11-24 |
| CA2540212A1 (en) | 2005-04-28 |
| DK1680525T3 (en) | 2014-07-14 |
| CN1890395A (en) | 2007-01-03 |
| EP2770081A3 (en) | 2014-11-05 |
| AU2004282496B2 (en) | 2010-11-11 |
| US20070029014A1 (en) | 2007-02-08 |
| RU2006115566A (en) | 2007-11-20 |
| JP4995570B2 (en) | 2012-08-08 |
| US7156932B2 (en) | 2007-01-02 |
| MXPA06003569A (en) | 2006-06-14 |
| EP2770080A2 (en) | 2014-08-27 |
| EP1680525A1 (en) | 2006-07-19 |
| RU2361009C2 (en) | 2009-07-10 |
| BRPI0415106B1 (en) | 2013-07-23 |
| US20050072500A1 (en) | 2005-04-07 |
| AU2004282496A1 (en) | 2005-04-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US7527702B2 (en) | Nickel-base alloys and methods of heat treating nickel-base alloys | |
| US6730264B2 (en) | Nickel-base alloy | |
| US20070044875A1 (en) | Nickel alloy and method of direct aging heat treatment | |
| US10837091B2 (en) | High temperature, damage tolerant superalloy, an article of manufacture made from the alloy, and process for making the alloy | |
| US20040033158A1 (en) | Precipitation hardened Co-Ni based heat-resistant alloy and production method therefor | |
| KR102332018B1 (en) | High temperature titanium alloy and method for manufacturing the same | |
| JP2002097537A (en) | Co-ni based heat resistant alloy and manufacturing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| AS | Assignment |
Owner name: ATI PROPERTIES, INC., OREGON Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CAO, WEI-DI;KENNEDY, RICHARD L.;REEL/FRAME:022364/0763 Effective date: 20031002 |
|
| STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
| FPAY | Fee payment |
Year of fee payment: 4 |
|
| FPAY | Fee payment |
Year of fee payment: 8 |
|
| MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 12TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1553); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 12 |